Flight vehicles including electrically-interconnective support structures and methods for the manufacture thereof

• US 8,826,640 B2
• Filed: 11/12/2010
• Issued: 09/09/2014
• Est. Priority Date: 11/12/2010
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Olden, Thomas A., Wrigglesworth, Walter
• Primary Examiner(s): Rodriguez, William H
• Assistant Examiner(s): Rivera, Carlos A
• Application Number:
  US12/945,440
• Publication Number:
  US 20120117941A1
• Time in Patent Office: 1,397 Days
• Field of Search: 602/53, 602/55, 602/56, 244/39.21, 244/39.12, 244/3.21, 244/12.4, 244/12.5, 239/265.15, 239/265.19
• US Class Current: 60/253
• CPC Class Codes: B64G 1/26 using jets
• CPC Class Codes: B64G 1/403 Solid propellant rocket engines
• CPC Class Codes: F42B 10/661 using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
• CPC Class Codes: Y10T 29/49346 Rocket or jet device making

Abstract

Embodiments of a flight vehicle are provided, as are embodiments of a method for manufacturing a flight vehicle. In one embodiment, the flight vehicle includes a solid-propellant rocket motor, control circuitry, and an electrically-interconnective support structure. The electrically-interconnective support structure includes a load-bearing frame and a plurality of electrical conductors embedded within the load-bearing frame. The solid-propellant rocket motor is mounted to the load-bearing frame, and the plurality of electrical conductors embedded within the frame electrically couples the solid-propellant rocket motor to the control circuitry.

Claims

1. A flight vehicle, comprising:

a solid-propellant rocket motor;

control circuitry; and

an electrically-interconnective support structure, comprising;

a singular load-bearing frame to which the rocket motor and the control circuitry are mounted such that the rocket motor and the control circuitry are non-rotatable relative to one another, the load bearing frame comprising first, second and third woven layers; and

a plurality of electrical conductors embedded within the load-bearing frame and electrically coupling the rocket motor to the control circuitry,

a first portion of the electrical conductors being disposed on a surface of the third woven layer between the second and third woven layers, and

a second portion of the electrical conductors being disposed on a surface of the second woven layer between the first and second woven layers.

2. A flight vehicle according to claim 1 further comprising a rocket motor array including the rocket motor and mounted around the load-bearing frame.

3. A flight vehicle according to claim 2 wherein the rocket motor array is circumferentially-spaced about a longitudinal axis of the flight vehicle.

4. A flight vehicle according to claim 1 wherein the electrically-interconnective support structure has a generally cylindrical outer geometry.

5. A flight vehicle according to claim 1 wherein the rocket motor is mounted to an intermediate portion of the load-bearing frame, and wherein the control circuitry is mounted to a first end portion of the load-bearing frame.

6. A flight vehicle according to claim 5 wherein the first end portion includes a cavity in which the control circuitry is disposed.

7. A flight vehicle according to claim 5 further comprising an optical sensor system mounted to a second end portion of the electrically-interconnective support structure substantially opposite the control circuitry.

8. A flight vehicle according to claim 1 wherein the load-bearing frame comprises an opening through which the rocket motor extends.

9. A flight vehicle according to claim 8 wherein the load-bearing frame comprises an annular wall, and wherein the opening comprises a radial opening formed in the annular wall.

10. A flight vehicle according to claim 8 wherein the plurality of electrical conductors comprise a point-of-contact formed on the load-bearing frame proximate the radial opening and electrically coupled to the rocket motor.

11. A flight vehicle according to claim 1 wherein the first, second and third woven layers of the load-bearing frame comprises a fiber reinforced polymer.

12. A flight vehicle, comprising:

an electrically-interconnective support structure, comprising;

a singular load-bearing frame having an outer annular wall and comprising first, second and third woven layers; and

a plurality of electrical conductors embedded within the load-bearing frame, a first portion of the electrical conductors being disposed on a surface of the third woven layer between the second and third woven layers and a second portion of the electrical conductors being disposed on a surface of the second woven layer between the first and second woven layers;

a solid-propellant rocket motor, comprising;

a rocket motor casing extending through the outer annular wall;

a solid propellant disposed within the rocket motor casing; and

an ignition device disposed within the rocket motor casing adjacent the solid propellant and electrically coupled to the plurality of electrical conductors embedded within the load-bearing frame,

wherein the rocket motor and control circuitry to which the rocket motor is coupled are mounted to the singular load-bearing frame such that the rocket motor and the control circuitry are non-rotatable relative to one another.