Solid pyrotechnic compositions for projectile base-bleed systems

• US 5,056,436 A
• Filed: 10/03/1988
• Issued: 10/15/1991
• Est. Priority Date: 10/03/1988
• Status: Expired due to Fees

• Current Assignee: Loral Aerospace Corp. (MHR Holdings LLC (New York))
• Original Assignee: Loral Aerospace Corp. (MHR Holdings LLC (New York))
• Inventors: Greene, Robert W.
• Primary Examiner(s): Miller, Edward A.
• Application Number:
  US07/252,626
• Time in Patent Office: 1,107 Days
• Field of Search: 102/490, 102/501, 102/374, 149/19.7
• US Class Current: 102/490
• CPC Class Codes: C06B 29/00 Compositions containing an inorganic oxygen-halogen salt, e.g. chlorate, perchlorate
• CPC Class Codes: C06B 31/00 Compositions containing an inorganic nitrogen-oxygen salt
• CPC Class Codes: F42B 10/40 with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles

Abstract

The invention is directed to a solid, pyrotechnic composition as a base-bleed composition for reducing the base-drag of non-self-propelled projectiles. The composition comprises a oxygenated hydrocarbon component and an oxidizing agent component.

Claims

1. A method for reducing the base-drag of a non-self-propelled projectile comprising the steps of:

providing a non-self-propelled projectile having a cavity wherein and fluid communication between said cavity and the near wake zone at the base of said projectile;

loading said cavity with a pyrotechnic composition that provides upon burning of said composition a low mass flow of gaseous combustion products in the near wake zone of said projectile, said low mass flow of combustion products being sufficient to increase the base pressure in the near wake zone and decrease the base-drag of said projectile, wherein said pyrotechnic composition comprises;

(A) oxygenated hydrocarbon component selected from the group consisting essentially of dehydroacetic acid, sorbital, ascorbic acid, adipic acid, lactose, glucose, and mixtures of any of them, said oxygenated hydrocarbon component having a melting point above 90°

C.; and

(B) oxidizing agent component; and

reacting said oxygenated hydrocarbon component with said oxidizing agent component during at least a portion of flight of said projectile.

2. The method for reducing base-drag according to claim 1, wherein said composition comprises (A) and (B) in amounts sufficient to oxidize substantially all of the carbon atoms in said oxygenated hydrocarbon component to carbon dioxide.

3. The method for reducing base-drag according to claim 1, wherein said oxygenated hydrocarbon component has a melting point above about 110°

C.

4. The method for reducing base-drag according to claim 3, wherein said oxygenated hydrocarbon component has a melting point above about 180°

C.

5. The method for reducing base-drag according to claim 1, wherein said oxidizing agent component is selected from the group consisting essentially of nitrates, nitrites, chlorates, chlorites and perchlorates, and mixtures of any of them.

6. The method for reducing base-drag according to claim 5, wherein said oxidizing agent component is potassium perchlorate.

7. The method for reducing base-drag according to claim 1, wherein said low mass flow of gaseous combustion products is provided during a considerable portion of said non-self-propelled projectile flight time.

8. The method for reducing base-drag according to claim 7, wherein said low mass flow of gaseous combustion products is provided during at least about 30% of said non-self-propelled projectile flight time.

9. The method for reducing base-drag according to claim 8, wherein said low mass flow of gaseous combustion products is provided for at least about 50% of said non-self-propelled projectile flight time.

10. The method for reducing base-drag according to claim 9, wherein said low mass flow of gaseous combustion products is provided for at least about 80% of said non-self-propelled projectile flight time.