Aeronautics and astronautics – Missile stabilization or trajectory control – Externally mounted stabilizing appendage
Patent
1998-04-13
2000-06-13
Tudor, Harold J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Externally mounted stabilizing appendage
F42B 1014
Patent
active
060738790
DESCRIPTION:
BRIEF SUMMARY
TECHNICAL FIELD
The invention relates to field of rocket or missile technology, in particular to guided rockets, and can be used for various types and classes of rockets with lattice control surfaces; the invention concerns also a lattice control surface and can be used in control systems.
PRIOR ART OF THE INVENTION
Rockets are known which are made according to standard aerodynamic design, containing a propulsion system located in the body and control and guidance apparatus, fixed wings and lattice control surfaces of the control system, located on the body in regular intervals around its centerline and having lifting surfaces formed by planes.
Such a rocket with a different degree of disclosure was described in the following journals: "FLIGHT INTERNATIONAL" on Mar. 4-10, 1992, N4308, page 24 . . . 25, "FLIGHT INTERNATIONAL" on Mar. 11-17, 1992, N4309, page 15 and the most completely in the journal "KRYL'YA RODYNY" (in Russian), N8-93 (Colour picture and page 26).
Realization of a rocket with lattice control surfaces allows use of small-sized and low energy consuming drives in control systems, which provides decreased mass and dimensional characteristics of the rocket as a whole.
At present lattice control surfaces of various shapes and different design are used in control systems of rockets of different kinds and purposes. One of the basic characteristics of a lattice control surface in distinction from a monoplane is the following. In a monoplane design the load-carrying components are located under the skin and do not participate in the creation of aerodynamic forces. In a lattice control surface the load-carrying components are in exposed to the air or fluid flow and, hence, form the lifting area of the control surface, i.e. the elements of a lattice control surface perform a double role--both load-carrying design and aerodynamic surface. A consequence of this is the fact that the lifting force (lift) of a lattice control surface is several times higher than the lift of a monoplane control surface of equal volume.
The ability to decrease lattice control surface volume, in comparison with the volume of a monoplane control surface, results in essential reduction of a drag force (drag) from the oncoming flow, since the lattice control surface actually represents a thin-walled truss, having, in addition to other positive features, advantages in comparison with a monoplane design in rigidity and weight parameters.
The lattice control surface of the rocket with arrangement of the lattice planes at angle of 45.degree. to the frame is known (so-called cellular design), (see B. M. Belotserkovsky, L. A. Odnovol etc., Reschetchatye Kryl'ya; Moscow, "Mashinostroeniye", 1985 (in Russian), page 300, FIG. 12.2, B).
The noted lattice control surface contains a load-carrying frame of the rectangular shape, including side bars, root and tip planes and units of attachment of the control surface to the control drive shaft, and the set of the planes with various thickness located inside the frame, forming a lattice as honeycomb. Various thickness of the planes is provided by strengthening of some planes within the limits of the surface scope. Jointing of the planes in a lattice is made by a standard technology by means of counter slots with subsequent soldering. The blanks of the planes are made with wedge-shaped sharpening at front and rear edges (see the same source, pages 216 . . . 223).
The advantages of the above specified control surface are determined by general advantages of lattice control surfaces in comparison with conventional monoplane control surfaces. At the same time, the design of the known lattice control surface has a number of disadvantages, including: frame and the lattice itself) the inclusion of thickened planes along the span of a control surface results in relative increase of a drag force for the given control surface; sharpened at the leading edge and not soldered, areas of slots are exposed. In some modes of flight this can result in the appearance of a shock wave in the non-soldered areas,
REFERENCES:
patent: 2846165 (1958-08-01), Axelson
patent: 3047259 (1962-07-01), Tatnall et al.
patent: 3064930 (1962-11-01), Chevalier
patent: 3944168 (1976-03-01), Bizien et al.
patent: 4560121 (1985-12-01), Terp
patent: 4641802 (1987-02-01), Zalmon et al.
patent: 4660786 (1987-04-01), Brieseck et al.
patent: 4884766 (1989-12-01), Steinmetz et al.
patent: 5048773 (1991-09-01), Washington et al.
patent: 5114095 (1992-05-01), Schroppel et al.
patent: 5192037 (1993-03-01), Moorefield
patent: 5549065 (1996-08-01), Cipolla et al.
patent: 5551364 (1996-09-01), Cipolla et al.
patent: 5584448 (1996-12-01), Epstein et al.
patent: 5642867 (1997-07-01), Klestadt
S. M. Belotserkovsky, "Reshetchatye Krylya," 1985, "Mashinostroenie," pp. 10-12, Figs. B1-B3, B5.
Flight International, Mar. 4-10, 1992, N4308, pp. 24-25.
Flight International, Mar. 11-17, 1992, N4309, p. 15.
Kryl'va Rodyny, N8-93 (p. 26 and picture), Date Unknown.
Belyaev Vladimir Nikolaevich
Bogatsky Vladimir Grigorievich
Bychkov Evgeny Alexandrovich
Dreer Daniil Leonidovich
Emelianov Vladimir Petrovich
Garrison David L.
Tudor Harold J.
Vympel State Machine Building Design Bureau
LandOfFree
Rocket with lattice control surfaces and a lattice control surfa does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Rocket with lattice control surfaces and a lattice control surfa, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Rocket with lattice control surfaces and a lattice control surfa will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-2062054