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HYPERSONIC MISSILES FOR LONG-RANGE PRECISION STRIKE

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Affordable Hypersonic Missiles for Long-RangePrecision Strike

Michael E. White and Walter R. Price

he United States’ current and planned weapons systems for strike warfare aredeficient in their ability to attack time-critical targets at long range. Hypersonic air-breathing propulsion may be an enabling technology to remedy this deficiency. Arevolutionary strike warfighting capability could be supplied by coupling hypersonic air-breathing propulsion into a long-range missile and incorporating other recenttechnology advances such as Global Positioning System guidance, greatly improvedtargeting capability, and improved lethality payloads (e.g., smart submunitions andkinetic-energy penetrators). The Defense Advanced Research Projects Agency hasinitiated the Affordable Rapid Response Missile Demonstrator Program to develop aconcept for an affordable hypersonic long-range cruise missile and to demonstrate it inflight for the first time. A firm program requirement is that the eventual average “unitflyaway” price of the missile concept demonstrated be $200,000 or less. This articlediscusses the overall program goals and approach and briefly describes the technologybeing pursued. (Keywords: Hypersonic, Missile, Ramjet, Scramjet.)

INTRODUCTIONThe development of a long-range, high-speed missile

utilizing hypersonic aeropropulsion technology offers anopportunity to dramatically change the warfighter’sability to respond to a broad range of threats. A hyper-sonic cruise missile (a missile that flies at speeds greaterthan 5 times the speed of sound) possesses a uniquecombination of speed, lethality, survivability, andrange. It presents the tactical warfighter with unprec-edented capability to respond to long-range threatssuch as time-critical, hardened, buried, and heavilydefended targets. Developers of a long-range, precision-strike weapon system based on a hypersonic cruise missile

JOHNS HOPKINS APL TECHNICAL DIGEST, VOLUME 20, NUMBER 3 (1

must consider numerous factors required to conduct asuccessful mission, including

• Overall missile kinematic performance• Launch platform compatibility• Adequate command, control, communications, com-

puters, intelligence, surveillance, and reconnaissance(C4ISR)

• Targeting requirements• Accurate guidance and navigation• Survivability• Payload lethality

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M. E. WHITE AND W. R. PRICE

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Hypersonic cruise missiles typically fly at altitudesxceeding 90,000 ft, with cruise speeds of 6000 ft/s orore. They can be powered all the way to the target,hich allows significant trajectory flexibility and veryigh impact velocities. Such flexibility and impactelocity give the missile a unique capability againstime-critical, heavily defended, and hardened or buriedargets. The altitude and speed during cruise make theissile highly survivable and greatly reduce the time of

light relative to subsonic cruise missiles. Furthermore,he survivability permits a simple “up and over” trajec-ory, dramatically reducing prelaunch timelines for mis-ion planning. High velocities at impact greatly in-rease the kinetic energy available to defeat hardenedr buried targets. For targets that are sheltered from theirection of attack, the ability to strike from any direc-ion improves lethality relative to ballistic missiles.

These missile capabilities raise numerous technicalhallenges associated with propulsion and aerothermalurvivability that are briefly discussed here. White1

ives more detail on the benefits and the technicalhallenges of a long-range, precision-strike weaponystem based on a hypersonic cruise missile. Two of theost critical issues associated with the development of

uch a weapon system are the flight test demonstrationf a viable hypersonic missile and the affordable pro-uction of such a missile.

The development of a long-range, high-speed

missile utilizing hypersonic aeropropulsion

technology offers an opportunity to dramat-

ically change the warfighter’s ability to respond

to a broad range of threats.

ROGRAM DESCRIPTIONThe Affordable Rapid Response Missile Demonstra-

or (ARRMD) Program of the Defense Advancedesearch Projects Agency (DARPA) began in fiscal998. Its objective is the flight test demonstration of long-range hypersonic cruise missile concept designedo meet the most effective set of performance objectiveshile constrained to a firm program affordability

equirement.

esign-to-Cost RequirementThe design-to-cost requirement of the ARRMD

rogram is an average unit flyaway price (AUFP) of200,000, in FY98 dollars, for a single-lot productionurchase of 3000 missiles. The AUFP requirement isirm: the missile design is to be optimized with respecto a list of performance goals and thresholds to max-mize weapon effectiveness within the $200,000 cost

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constraint. To meet the unit cost constraint, the con-tractor is permitted to employ “best commercial prac-tices” to the extent necessary and to apply a learningcurve consistent with experience in past missile pro-duction programs. The baseline $200,000 missile priceis for air launch of the missile. It includes the air ve-hicle, all subsystems, and a basic warhead. The AUFPfor the ship-launched variant is to be proportionallyhigher to account for the larger rocket booster needed.

Performance GoalsThe missile concept demonstrated in the ARRMD

Program must meet the most effective set of programperformance goals within the defined AUFP require-ment. Within this list of program goals are criticalthresholds on range and speed. The missile conceptsalso must include the use of logistically suitable fuels.The ARRMD performance goals are as follows:

• Powered range of 600 nmi, with a minimum thresholdof 400 nmi

• Time to target of less than 7 min at a range of 400 nmi• Aim-point ground impact error of less than 35 ft• Ground impact velocity of 4000 ft/s• Survivability against surface-to-air missile (SAM)

threats in 2005 and beyond• Compatibility with Air Force and Navy tactical fight-

ers; internal carriage on Air Force strategic bombersand on Navy Vertical Launch Systems and CanisterLaunch Systems

• Mission flexibility in a tactical environment• Minimum payload weight of 250 lb, with warhead

modularity for smart submunitions, unitary muni-tions, and kinetic energy penetrators

• Use of logistically suitable liquid hydrocarbon fuels• Capacity for at least 10 years of storage without

servicing (i.e., a “wooden round” missile)

Program Execution StrategyThe ARRMD Program is being executed in two

phases. Phase 1 is an 18-month risk reduction and con-cept validation phase. Phase 2 will focus on the flighttest demonstration. The purpose of Phase 1 is to reducerisk in the areas of affordability and flight vehicle via-bility for two candidate missile concepts. A series ofcomponent demonstrations is proving the viability ofthe critical low-cost manufacturing techniques thatwill enable the candidate missile concepts to meetthe $200,000 AUFP requirement. Effort also is beingfocused on developing cost models and increasing thefidelity of the estimates associated with manufacturingthe missile components and integrating the missile sys-tem. The missile designs will be evolved through a pre-liminary design review, and the performance and oper-ability of the candidate flight vehicle concepts will be

NS HOPKINS APL TECHNICAL DIGEST, VOLUME 20, NUMBER 3 (1999)


demonstrated in a series of wind tunnel tests. These testswill measure the operating characteristics of criticalengine components, integrated engines, high-tempera-ture materials, and actively cooled structures.

The data gathered in Phase 1 will supply the criticalaffordability, performance, and operability informationrequired for progressing to the flight test demonstrationin Phase 2. Should the Phase 1 data support the viabilityand affordability of the proposed concepts, DARPA willdecide whether to proceed to Phase 2.

At the start of Phase 2, DARPA will select the mostpromising vehicle concept for the flight demonstration.The program flight test demonstration phase will last30 months. It will consist of the detailed design of theselected flight vehicle, flight demonstration of themissile’s aeropropulsion performance capabilities, andrefinement and large-scale demonstration of manufac-turability processes. A final affordability assessment willbe made to substantiate the $200,000 AUFP, and op-erational utility of the missile will be assessed.

The ARRMD TeamThe DARPA Tactical Technology Office, with Lieu-

tenant Colonel Walter Price as the Program Manager,is executing the ARRMD Program. The Air Force Re-search Laboratory (AFRL), which is serving as thecontracting agent for DARPA, has established a singleagreement with the Boeing Company to execute bothphases of the ARRMD Program. Boeing has been di-rected to pursue two candidate missile concepts withequal vigor and has primary subcontracts for propulsionwith Aerojet and Pratt & Whitney (P&W) to developthe two candidate vehicle concepts. APL is serving asDARPA’s lead technical advisor for program executionand is supporting flight vehicle design, affordabilityassessment, and warfighting benefit analysis. The AFRLand the Air Force Aeronautical Systems Command arealso providing technical program support.

The Candidate Missile ConceptsThe Phase 1 activity will bring two candidate missile

concepts proposed by Boeing to maturity. Boeing andP&W developed the first concept based on integratingpropulsion technology developed by P&W under theAir Force Hypersonic Technology (HyTech) Pro-gram.2,3 The HyTech-based propulsion system is inte-grated into a flight vehicle based on a “waverider”design (Fig. 1). (A waverider is a vehicle having a highlift-to-drag ratio due to shock wave pressurizationeffects at supersonic speeds.) The engine is rectangularand integrated into the underside of the flight vehicle,utilizing the underside compression for the inlet. Theinlet feeds a rectangular combustor containinginnovative air-breathing pilots that allow efficient burn-ing of a hydrocarbon fuel in a predominantly supersonic


(a)

(b)

(c )

(d)

Figure. 1. Waverider-based Affordable Rapid Response MissileDemonstrator. This concept is for a missile that uses endothermicfuel, has an actively cooled structure, and is capable of Mach 4 to8 operation: (a) vehicle with side-mounted boosters, (b) rectangu-lar integrated engine flow path, (c) air-breathing pilot, (d) pilotoperating on hydrocarbon fuel.

combustor. The engine’s combustor is actively cooledusing the liquid endothermic fuel. The engine’s nozzleis integrated into the aft portion of the underside of thevehicle. The cruise vehicle is boosted to the Machnumber at which the air-breathing engine takes overfrom the rocket booster. These boosters are side-mounted for integration onto aircraft launch platforms.

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When the missile is integrated with naval ship plat-forms, the side-mounted boosters are replaced by atandem booster sized to meet the constraints of thevertical and canister launch systems. More details onthis concept are presented in the section on TechnicalChallenges.

The second missile concept was developed by Boe-ing and Aerojet. It is based on dual-combustor ramjet(DCR) technology originally developed by the Navyfor surface-to-air applications under the Navy SurfaceLaunched Missile Technology Program (Fig. 2).4 Thisconcept is for an axisymmetric missile with multipleinward-turning scoop inlets located in the compressionfield of a conical forebody. These inlets split the air tofeed a subsonic dump combustor and a tandem super-sonic combustor. All of the fuel is added to the subsoniccombustor, which heats and partially cracks the fuel.The fuel-rich effluent provides the core flow for mixingwith the annular supersonic inlet supply in the super-sonic combustor. This design burns unprocessed liquidhydrocarbon fuel and relies on high-temperature mate-rials and insulation for the engine and airframe struc-ture. A slip-in booster for the air-launched configura-tion boosts the missile to a take-over Mach number. Atandem booster is used for ship-launched versions. (Seealso the section on Technical Challenges.)

Coordination with DoD Science and TechnologyPrograms

The ARRMD Program is not a technology develop-ment program; rather, it is a program to demonstratestate-of-the-art technology being developed by theNavy and Air Force. The Office of Naval Research(ONR) is executing the Hypersonic Weapon Technol-ogy (HWT) Program to mature the suite of criticalcomponent technologies that specifically enable along-range strike missile and to demonstrate them. Thisprogram is a coordinated effort between the Naval AirWarfare Center Weapons Division at China Lake,APL, and the Naval Surface Warfare Center atDahlgren, Virginia. China Lake is responsible for pro-gram management, guidance and control, and airframetechnologies. APL is responsible for propulsion technol-ogies, and Dahlgren is responsible for ordnance tech-nology. Under the HWT propulsion program, the near-term focus is the DCR engine, and the HWTpropulsion tasks have been fully coordinated withARRMD Program efforts. In addition, HWT ordnancetechnology being developed for multifunctionwarheads can be applied to the weapon concepts underthe ARRMD Program.

The AFRL has contracted with P&W under theHyTech Program to develop hydrocarbon-fueled scram-jet propulsion technology for Mach 4 to 8 applications.Such applications might include a long-range strike

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missile, global reach aircraft, or even an interim stagefor access to space. The broad range of applications forthe HyTech technology is enabled by the use of anendothermic hydrocarbon fuel and an actively cooledstructure. The Boeing/P&W waverider concept for theARRMD Program uses this HyTech technology andrelies heavily on that program’s technology develop-ment efforts.

To cover coordination between the Navy and AirForce hypersonic technology programs and theDARPA flight demonstration program, a Memoran-dum of Understanding has been established. Initially,DARPA and ONR established and signed such amemorandum stating that “their programs are to beintegrated in a manner that best permits the accom-plishment of the overall objective to field a hypersoniccruise missile.” The memorandum notes that “DARPAwill look to the ONR Hypersonic Weapon TechnologyProgram to help provide the technology basis to drawfrom during the execution of the ARRMD program,”and provide “continual technology evolution essentialto the eventual development of a viable weapon sys-tem.” It also affirms that the “DARPA program address-es the critical objectives of weapon manufacturabilityand affordability, and provides an essential near-termopportunity to demonstrate hypersonic missile technol-ogies in flight.” This memorandum was recently ex-panded to include the Air Force HyTech Program. Theexpanded memorandum states that “DARPA, ONR,and AFRL will coordinate their programs and establishan integrated technology roadmap supporting hy-personic weapons development,” and that “programexecution strategies for the ARRMD, HWT, andHyTech programs will be pursued that are mutually

Figure. 2. Dual-combustor ramjet–based Affordable Rapid Re-sponse Missile Demonstrator. This concept is for a missile thatuses conventional hydrocarbon fuels, has improved low-speedperformance and good hypersonic performance, is efficient fromMach 3 to above Mach 6, and is more efficient than a ramjet exceptat and near the ramjet design point. (M = Mach number, M0 =freestream Mach number, and Mci = combustor inlet Mach number.)

Inlet cover

Slip-in booster

Subsonic combustor

Supersonic combustor

ExitnozzleMex > 1

M < 1

M0 > 1

Mci > 1

Dual-combustor ramjet

Multiscoopinlet



supportive and integrated.” The fully integrated mem-orandum is currently awaiting signature.

Concept of OperationsThe technology being demonstrated under the

ARRMD Program will enable the development of anAffordable Rapid Response Missile (ARRM). TheARRM will be compatible with a large range of launchplatforms and will be able to use targeting informationderived from national and tactical surveillance assets.Utilizing a modular or multifunction warhead, theARRM is envisioned as having the capability to defeattime-critical, hardened, buried, and heavily defendedtargets. Figure 3 depicts a baseline concept of opera-tions for employment of a notional hypersonic strikeweapon system concept based on the ARRM.

For the baseline concept of operations, the target isidentified and located using a variety of potential sur-veillance assets, either in-theater (e.g., Joint Surveil-lance and Targeting Attack Radar System [JSTARS],Global Hawk, Dark Star) or spaced-based (e.g., DefenseSupport Program [DSP], Space Based Infrared System[SBIRS], or Discoverer II). The target location is pro-vided in the form of Global Positioning System (GPS)coordinates to a strike warfare commander via satellitecommunications links. This GPS target location isuploaded to the missile, and the missile is launched atthe threat. During flyout, improved targeting informa-tion can be transmitted to the missile using securesatellite communications links, should such informationbe available from either national space-based or


in-theater surveillance assets. The rapid-response mis-sile flyout is done at hypersonic speeds, and once in thetarget area, the missile terminal maneuver is tailored tothe type of target being attacked. For relocatable targetswhose location error is such that submunitions are re-quired, the missile slows, descends to deploy an appro-priate submunition payload, and attacks the targetbefore leaving the area. For fixed hard or buried targets,the ARRM carries a kinetic-energy penetrator and divesvertically to the target at high speed. For soft targets,the same high-velocity terminal dive is envisioned withdeployment of a high-explosive or area munitions pay-load. Figure 4 shows the critical components of anARRM weapons system concept.

TECHNICAL CHALLENGES

Hypersonic MissileA number of critical technical challenges are asso-

ciated with demonstration of a hypersonic cruise mis-sile. At a top level, many of the challenges are common,regardless of the missile concept being developed, butoften the approach to these top-level challenges createsa concept-specific set of technical problems. Again, inthe ARRMD Program, affordability is a firm missiledesign requirement. Thus, ARRMD will focus ondemonstrating an affordable flight vehicle to make along-range hypersonic weapon system possible.

Perhaps the most challenging issue in developing amissile for sustained hypersonic flight is the ability to

Figure. 3. Concept of operations for a hypersonic strike weapon system based on the Affordable Rapid Response Missile (ARRM) understudy. The system holds deep targets at risk and allows a short time of flight to fleeting targets.

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National assets Hypersonic cruise missile

Multiple launch platforms

GPS/IMU guidance Secure satellite communications

Modular payload

Figure. 4. The hypersonic strike weapons system concept based on the ARRMD.(GPS = Global Positioning System; IMU = inertial measurement unit.)

deal with the extreme thermal environment. Flight atspeeds above Mach 6 results in missile skintemperatures that exceed 1000oF, leading edge and inletduct temperatures that exceed 2000oF, and combustorand nozzle temperatures in excess of 4000oF if there isno active cooling (Fig. 5).5 The approach to survivalin this thermal environment varies depending on thespecific missile concept and missile component. Formost of the exterior surfaces of the missile, the use ofhigh-temperature materials with or without thermal

420 JOHNS HOPKINS APL TECHN

barrier coatings is generally ade-quate. Missile components direct-ly exposed to the air stream, suchas control surfaces and inlets, needspecial attention because of sweptand unswept leading edges and theresulting shock interactions. In-side the missile, critical sub-systems, including payload, elec-tronics, and the fuel system, musteither be protected from the ex-treme temperatures or designed tohandle them.

By far the most stressing ther-mal challenge is the combustor.How the thermal environment isovercome in the combustor is di-rectly linked to another criticaltechnical challenge: getting a lo-gistically suitable liquid hydrocar-bon fuel to burn efficiently in asupersonic stream. The twoARRMD concepts approach thisproblem in dramatically differentways. A brief description of eachconcept missile’s operation illus-trates this difference.

The waverider hypersonicmissile concept discussed earlier(Fig. 1) incorporates a propulsionapproach having its origins inwork sponsored by the Navy andinvolving NASA Langley Re-search Center and United Tech-nologies Research Center. Re-searchers at United Technologiesdeveloped the rectangular com-bustor configuration that embedsa small, subsonic combustion, air-breathing pilot on the wall of thecombustor. The pilot captures asmall amount of flow and burns asmall amount of fuel. Its exhaustanchors the supersonic combus-tion in the primary combustor,where the rest of the fuel is added.

This engine configuration requires the liquid hydro-carbon fuel to be vaporized upon injection. Anendothermic fuel is used, and backside heat exchangerpanels provide a vaporized, partially cracked product tothe combustor. This approach also utilizes the heatexchanger to cool the combustor walls.

The actively cooled combustor can control the walltemperature and offers the potential to operate atspeeds on the order of Mach 8, but the actively cooledstructure and the associated fuel system must be built

ICAL DIGEST, VOLUME 20, NUMBER 3 (1999)


affordably. Reasonable combustor performance hasbeen demonstrated under the HyTech Program forMach numbers ranging from 4 to 8.

The primary technical challenges of the waveriderapproach include

• Affordable integration of the requisite missile sub-systems to permit cold start of the engine, inlet start-ing, and control of the heated fuel

• Integration and affordability of the rocket boosters• Controllability of the air vehicle throughout the

flight envelope

The ARRMD Program will benefit from continuingdevelopment work under the HyTech Program on theengine technology being utilized in the waveriderconcept. Under the ARRMD Program, the flight ve-hicle design will be developed to maturity and demon-strated through force and moment wind tunnel testing.Critical low-cost manufacturing approaches for thisconcept will be demonstrated.

The DCR-powered hypersonic missile concept(Fig. 2) combines features of a ramjet and a scramjetby embedding a subsonic dump combustor in the

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Cruise Mach number

Combustors

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Inlet ducts

Unsweptleadingedges

Nose tip

Sweptleadingedges

RadomesExternal

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Figure. 5. Steady-state temperature versus cruise Mach numberfor critical missile components at an 80,000-ft altitude.5


engine upstream of the supersonic combustor to act asa pilot. This pilot prepares the hydrocarbon fuel forburning in the supersonic combustor. Approximately25% of the air passing through the engine is capturedby two inlets and ducted to an embedded subsonic dumpcombustor, where it is mixed and burned with all of thefuel. The resulting fuel-rich effluent then burns, withthe air stream captured and delivered to the tandemsupersonic combustor by four inward-turning scoopinlets. These inlets compress and wrap the flow into anannular dump plane at the same axial station as thesubsonic combustor exit. The combustion process thatstarts in the subsonic combustor is then completed inthe cylindrical supersonic combustor and exhaustedthrough the divergent exit nozzle.

This combustor arrangement allows a hypersonicmissile to use conventional hydrocarbon fuel with liq-uid injection. Because the combustion process does notrequire any additional energy added to the liquid fuel,the entire combustor can be passively cooled for a cruiseMach number of approximately 6.5.

The primary technical challenges of the DCR ap-proach include

• Development and implementation of affordable ma-terials that can withstand the extreme temperaturesin the subsonic and supersonic combustors, the sur-rounding inlet ducts, and the nozzle

• Affordable fabrication of the complex inlet and sub-sonic combustor assembly

• Engine sizing for operation from Mach 3 to 6.5• Missile packaging to permit carrying of adequate fuel

and an effective warhead

Leveraging the technology development and compo-nent demonstration effort for the DCR sponsored bythe Navy from 1977 to 1986 and continued under theHWT Program, Phase 1 of the ARRMD Program willdemonstrate critical, low-cost manufacturing tech-niques and integrated propulsion system performance.

Targeting, C4ISR, and the EndgameTargeting and lethality are essential elements of a

viable weapon system. The ARRMD Program is focusedon demonstrating a viable hypersonic strike missile. Itsproduct is the flight-test demonstration of a missile thatcan fly at least 400 nmi to within 35 ft of a defined aimpoint. Ultimately, however, a successful long-rangestrike requires the ability to accurately locate andidentify the desired target, transmit the targeting infor-mation to the shooter in a timely manner, and use theresult in a lethal endgame. Targeting accuracy and la-tency dictate important weapon system requirementsfor terminal sensors, guidance system accuracy, commu-nications for in-flight target updates, and weapon flyouttime. This is particularly true for mobile or relocatable

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targets that pose the most stressing threat for a numberof important system design parameters. Two factors arecrucial in establishing the capability to defeat time-critical mobile targets like tactical ballistic missilelaunchers:

1. The ability to detect and identify the target withenough accuracy to effectively direct a strike

2. The ability to get that information to the shooterwithin the required time

This targeting ability defines many of the other majorweapons system requirements, as well as the overallprobability of mission success.

Several options exist for targeting, and the assetsavailable for deployment depend largely on the circum-stances of the conflict. Potential targeting assets includesatellites, manned aircraft, unmanned aerial vehicles,special operations forces, and unattended ground sen-sors. This infrastructure is currently being developedindependently of high-speed missile development;many resources are being applied to the timely identi-fication of tactical ballistic missile launchers and othercritical short-dwell targets.

At long range, a hypersonic cruise missile

permits maximum leverage from this [target-

ing] infrastructure. It compresses by a factor

of 5 to 6 the time of flight of the weapon for

attack of the target.

At long range, a hypersonic cruise missile permitsmaximum leverage from this infrastructure. It compressesby a factor of 5 to 6 the time of flight of the weapon forattack of the target. The compression greatly reduces thetime that a given sensor suite and communications chan-nel must be dedicated to a single target. It is likely tosignificantly improve overall warfighting effectiveness.

Certain space-based surveillance assets may be ableto identify a tactical ballistic missile launch and estab-lish a projected launch location within the time andaccuracy required to meet mission objectives. This typeof targeting capability would permit the developmentof the least-expensive weapon: guidance and navigationcould be provided with a GPS-updated inertialnavigation system, and the weapon payload could bearea munitions or flechettes. However, if assets are notavailable to provide sufficient launch location accuracyfor effective weapon system operation, a terminal sens-ing capability may be necessary. In that case, eitheradditional off-board, in-theater assets are needed (un-manned aerial vehicles, JSTARS, etc.) to supply moreaccurate targeting information for terminal guidance, orthe missile design must incorporate an active terminal

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seeker, or a payload with a terminal sensor capability(i.e., smart submunitions) must be used.

To defeat short-dwell relocatable targets, theARRMD Program’s approach is to carry smart submu-nitions to the target, such as the Brilliant Anti ArmorSubmunition (BAT) or the Low Cost AutonomousAttack Submunition (LOCAAS). Critical technologychallenges include thermally protecting the submuni-tion payload during the mission and deploying it atconditions consistent with the flight envelope of thehigh-speed missile, which can include terminal speedsas high as Mach 3. For penetrator missions where thetarget location is relatively well known, the ARRM willbe designed to carry a 250-lb kinetic-energy penetratorpayload delivered at impact velocities up to 4000 ft/s.For relatively soft area targets whose locations are wellknown, area munitions will be carried.

Launch Platform CompatibilitySome of the critical constraints imposed on the

design of a viable hypersonic weapon concern integra-tion with the launch platform. The ARRMD Programhas an objective of compatibility with a wide range oflaunch platforms. The missile weight is constrainedmost severely by the F/A-18 aircraft. Its length is con-strained most severely by the internal rotary rack onthe B-52 and B-1 strategic bombers. Geometric con-straints are imposed by the square cells of the NavyVertical Launch System on surface ships, the circularcross section of the Navy Canister Launch Systemaboard submarines, and the rotary rack on the bombers.In addition, the rocket boosters must meet insensitivemunitions constraints and firing limitations aboardships.

SUMMARYThe DARPA ARRMD Program is under way to

develop, and for the first time demonstrate in flight, ahypersonic cruise missile concept. The concept has asa firm requirement that the eventual AUFP not exceed$200,000. The only firm requirement for the missiledesign is affordability. Two candidate missile conceptsare being developed by Boeing to achieve capabilitygoals that include accuracy (35 ft), long range (600nmi), minimum time to target (7 min at 400 nmi),survivability, and robust launch platform compatibility.The missile must also be logistically suitable for thecomplete set of launch platforms and effectively be a“wooden round.” The 18-month Phase 1 activity willdemonstrate the viability of the air vehicle designs ina series of wind tunnel tests, demonstrate the criticallow-cost manufacturing techniques, and refine afford-ability assessments. Should Phase 1 objectives be suc-cessfully accomplished, and should DARPA continue



the work, Phase 2 will include selection of a preferredvehicle configuration. The selected configurationwill go into a 30-month flight test demonstration phase.The ARRMD Program is being coordinated with, andrelies on, Air Force HyTech and Navy HWT Programefforts.

REFERENCES1 White, M. E., “Hypersonic Cruise Missiles for Long-Range Precision Strike,”

in Proc., 1997 Precision Strike Technology Symp., Laurel, MD, pp. 103–116 (8–9 Oct 1997).


2 Bauer, C., “Scramjet Component Technology—A Program Summary,” inProc. 1997 JANNAF 34th Airbreathing Propulsion Subcommittee Meeting, WestPalm Beach FL, Publ. 666, Vol. 2, pp. 43–53 (27–30 Oct 1997).

3Mercier, R. A., and Ronald, T. M. F., “Hypersonic Technology (HyTech)Program Overview,” in Proc., 8th Int. Aerospace Planes and Hypersonic Systemsand Technologies Conf., AIAA 98-1566, Norfolk, VA (27–30 Apr 1997).

4 White, M. E., “Quick-Reaction, Deep-Strike Weapons System Concept,” inProc., 1996 JANNAF Propulsion Meeting, Albuquerque, NM, Publ. 654, Vol. 2,pp. 1–4 (Dec 1996).

5 Newman, R. W., “Oxidation-Resistant High-Temperature Materials,” JohnsHopkins APL Tech. Dig. 14(1), 24–28 (1993).

ACKNOWLEDGMENT: This work was performed under contract MDA972-96-D-0002, Task VRF01, with the Defense Advanced Research Projects Agency,Arlington, Virginia.

THE AUTHORS

MICHAEL E. WHITE joined APL in 1981 after receiving B.S. and M.S. degreesin aerospace engineering from the University of Maryland. He was appointed tothe Principal Professional Staff in 1991. Mr. White is currently the Program AreaManager for Advanced Vehicle Technologies in the Milton S. EisenhowerResearch and Technology Development Center. He has an extensive backgroundin aerospace engineering, with particular emphasis on high-speed aerodynamicsand propulsion. His experience includes the application of computational toolsto the design and analysis of high-speed vehicles and the experimentalassessment of hypersonic air-breathing propulsion systems. In addition, he hasconsiderable experience in program and line management gained through hisroles as APL Program Manager for the National AeroSpace Plane Program andAssistant Supervisor of the Propulsion Group. His e-mail address [email protected].

WALTER R. PRICE was commissioned and granted a B.S. in aerospaceengineering from North Carolina State University in 1979; he received an M.S.in aerospace management from Embry-Riddle Aeronautical University in 1996.Lieutenant Colonel Price flew for 5 years as a KC-135 navigator and then servedas Argus Program Manager and Flight Commander for the highly modifiedC-135 optical imaging aircraft. He also served as Director of Test Operations,4950TW/DOBT, managing a team of program managers for Argus, InfraredSignatures, Satellite Communications, Open Skies, and Big Crow (ECM/ECCM) aircraft. As Vehicle Design and Engine Component Program Managerfor the National AeroSpace Plane, he led a team that produced the first-everMach 10–16 scramjet combustion data. He is currently DARPA’s ProgramManager for the Miniature Air Launched Decoy Advanced Concept TechnologyDemonstrator and the Affordable Rapid Response Missile Demonstrator. His e-mail address is [email protected].

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