Defense Technical Information Center Compilation Part Notice ADPO 10957

  • Eugene L. Fleeman

Abstract

Executive Summary This paper provides an assessment of the state-of-the-art and design considerations of missile/aircraft integration for future precision strike missile systems. Benefits of missile/aircraft integration include compatibility with a broader range of aircraft carriage platforms, unrestricted carriage envelope, safe and accurate store separation, and enhanced survivability for the aircraft platform. Technologies and design considerations are grouped into the following discussion areas: "* Missile factor of safety compatibility. Assessments in this area include structural design factor of safety, carriage flight loads, and design specification of the carriage flight environment. "* Missile carriage and launch compatibility. Assessments in this area include launch platform compatibility constraints, firepower, light weight logistics, launcher alternatives, compressed carriage, standard suspension requirements, and safe separation. "* Survivability (missile observables/insensitive munitions) compatibility. Assessments in this area include internal carriage, reduced observable plumes, and insensitive munitions. Introduction Missile/aircraft integration sets constraints on the missile that must be considered early in the design development process, as illustrated in Figure 1. Moreover, the design process requires iteration to harmonize the outputs from the diverse areas of mission/scenario definition, missile requirements, aircraft integration, missile concepts, and technologies. In a few cases it may be possible to modify a launch platform to accommodate a new missile, but in most cases this is not an option. Generally the launch platform is a constraint that drives the missile design. For example, AMRAAM was originally developed as a light weight radar missile for carriage on the wing tips of the F-16, which has a 300 pound weight limit. Later, AMRAAM was modified to a compressed carriage configuration (clipped wings and tails) to better accommodate internal carriage in the F-22 center weapons bay. Precision strike missiles are driven as much by launch platform compatibility as other measures of merit. Weapon compatibility with all launch platforms has high payoff in the neckdown benefit cost savings of fewer missile logistics systems. Figure 2 shows an example of how missile/aircraft integration impacts the design validation/technology development process. Launch platform integration is considered from the start of subsystem development activities, continuing as they evolve into a missile system. In the propulsion area, static firings and insensitive munition tests are conducted before a missile with a live rocket motor is fired from a launch aircraft. In the airframe area, wind tunnel testing includes not only the basic aerodynamic configuration development, but also store separation wind tunnel tests. In the guidance & control area, the flight control system sensors, actuators, and electronics are analyzed to ensure safe separation as part of a missile modeling and simulation activity. The laboratory tests include environmental tests that simulate the operational temperature and vibration. The missile modeling and simulation activities include safe separation analysis. Similar to the propulsion area, the warhead has insensitive munition tests prior to firing a missile with a live warhead from an aircraft. Paper presented at the RTO SCI Lecture Series on "Technologies fJr Future Precision Strike Missile Systems ", held in Tbilisi, Georgia, 18-19 June 2001; Bucharest, Romania, 21-22 June 2001; Madrid, Spain, 25-26 June 2001; Stockholm, Sweden, 28-29 June 2001, and published in RTO-EN-018.

17 Figures and Tables

Cite this paper

@inproceedings{FleemanDefenseTI, title={Defense Technical Information Center Compilation Part Notice ADPO 10957}, author={Eugene L. Fleeman} }