×

zbMATH — the first resource for mathematics

Prediction of swerving motion of a dual-spin projectile with lateral pulse jets in atmospheric flight. (English) Zbl 1054.70021
Using the linear theory for a dual-spin projectile in atmospheric flight, closed form expressions are derived for swerving motion under the action of lateral pulse jets. Trajectory results generated by the linear theory and by a fully nonlinear seven degree-of-freedom dual spin projectile model agree favorably. In order to accurately predict the impact point using the analytical solution, the dual-spin projectile linear model must be updated periodically. Terminal impact point prediction degrades rapidly as the linear model update interval is increased beyond a critical value. Control authority (as defined by the change in impact location due to a pulse jet firing) steadily decreases as a function of projectile down range position.

MSC:
70P05 Variable mass, rockets
70Q05 Control of mechanical systems
PDF BibTeX XML Cite
Full Text: DOI
References:
[1] Guides, B.; Cooper, G., Closed form solution of finned projectile motion subjected to a simple inflight lateral impulse, ()
[2] Likins, P.W., Attitude stability criteria for dual-spin spacecraft, Journal of spacecraft and rockets, 4, 12, 1638-1643, (1967)
[3] Cloutier, G.J., Stable rotation states of dual-spin spacecraft, Journal of spacecraft and rockets, 5, 4, 490-492, (1968)
[4] Mingori, D.L., Effects of energy dissipation on the attitude stability of dual spin satellites, AIAA journal, 7, 10, 20-27, (1969) · Zbl 0175.21802
[5] Fang, B.T., Energy considerations for attitude stability of dual-spin spacecraft, Journal of spacecraft and rockets, 5, 5, 1241-1243, (1968)
[6] Hall, C.D.; Rand, R.H., Spinup dynamics of axial dual-spin spacecraft, Journal of guidance, control, and dynamics, 17, 1, 30-37, (1994)
[7] Or, A.C., Resonances in the design dynamics of dual-spin spacecraft, Journal of guidance, control, and dynamics, 14, 2, 321-329, (1991)
[8] Cochran, J.E.; Shu, P.H.; Rew, S.D., Attitude motion of asymmetric dual-spin spacecraft, Journal of guidance, control, and dynamics, 5, 1, 37-42, (1982) · Zbl 0541.70038
[9] Tsuchiya, K., Attitude behavior of a dual-spin spacecraft composed of asymmetric bodies, Journal of guidance, control, and dynamics, 2, 4, 328-333, (1979) · Zbl 0413.93009
[10] Yang, H.X., Method for stability analysis of asymmetric dual-spin spacecraft, Journal of guidance, control, and dynamics, 12, 1, 123-125, (1989)
[11] Viderman, Z.; Rimrott, F.P.J.; Cleghorn, W.L., Stability of an asymmetric dual-spin spacecraft with flexible platform, Journal of guidance, control, and dynamics, 14, 4, 751-760, (1991)
[12] Stabb, M.C.; Schlach, A.L., Pointing accuracy of a dual-spin satellite due to torsional appendage vibrations, Journal of guidance, control, and dynamics, 16, 4, 630-635, (1991)
[13] Smith, J.A.; Smith, K.A.; Topliffe, R., Feasibility study for application of modular guidance and control units to existing ICM projectiles, ()
[14] Costello, M.; Peterson, A., Linear theory of a dual-spin projectile in atmospheric flight, Journal of guidance, control, and dynamics, 23, 5, (2000)
This reference list is based on information provided by the publisher or from digital mathematics libraries. Its items are heuristically matched to zbMATH identifiers and may contain data conversion errors. It attempts to reflect the references listed in the original paper as accurately as possible without claiming the completeness or perfect precision of the matching.