Systems and methods for non-destructive testing of energetic materials

• US 9,970,920 B2
• Filed: 06/04/2015
• Issued: 05/15/2018
• Est. Priority Date: 06/04/2015
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Daoud, Sami
• Primary Examiner(s): Porta, David
• Assistant Examiner(s): FEIN, ABRA S
• Application Number:
  US14/730,784
• Publication Number:
  US 20160356758A1
• Time in Patent Office: 1,076 Days
• Field of Search: 250339, 250301
• CPC Class Codes: F02K 9/24 Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
• CPC Class Codes: F02K 9/96 characterised by specially adapted arrangements for testing or measuring
• CPC Class Codes: G01N 21/3563 for analysing solids; Preparation of samples therefor
• CPC Class Codes: G01N 21/359 using near infrared light
• CPC Class Codes: G01N 21/954 Inspecting the inner surface of hollow bodies, e.g. bores
• CPC Class Codes: G01N 33/22 Fuels; Explosives
• CPC Class Codes: G02B 23/2476 Non-optical details, e.g. housings, mountings, supports

Abstract

A non-destructive testing system for propellant for a rocket is provided. The system includes an insertion tube having a first end and a second end in addition to a support sleeve configured to mate with a casing of the rocket. The insertion tube includes a channel that extends from the first end to the second end of the insertion tube to receive a probe and also includes a probe tip generally disposed at the second end of the channel. The support sleeve includes an insertion tube opening configured to receive the insertion tube and allow the insertion tube to slide along the support sleeve.

Claims

1. A non-destructive testing system for propellant for a rocket comprising:

an insertion tube having a first end and a second end including;

a first channel extending from the first end to the second end of the insertion tube, the first channel being configured to receive an optical fiber probe that includes a first bundle of optical fibers and a second bundle of optical fibers;

a probe tip generally disposed at the second end of the first channel, wherein the first bundle of optical fibers extends into the insertion tube and terminates at a first end of the optical fiber probe at the probe tip to carry light to the probe tip, and wherein the second bundle of optical fibers extends into the insertion tube and terminates at the first end of the optical fiber probe at the probe tip to receive reflected light from the propellant; and

a support sleeve configured to mate to an ignition charge mount of the rocket, the support sleeve including an insertion tube opening configured to receive the insertion tube and allow the insertion tube to slide along the support sleeve.

2. The non-destructive testing system of claim 1, wherein the support sleeve includes a flange having at least one bolt hole.

3. The non-destructive testing system of claim 1, wherein the probe tip is configured to be removable from the insertion tube.

4. The non-destructive testing system of claim 1, wherein the probe tip is configured to extend towards the propellant and is one of an articulated probe tip and a 90 degree elbow probe tip.

5. The non-destructive testing system of claim 1, wherein the insertion tube further includes a compression fitting disposed at the first end of the first channel to hold the optical fiber probe in place.

6. The non-destructive testing system of claim 1, further comprising a receptacle configured to receive a second end of the optical fiber probe and optically couple the optical fiber probe to a Near Infrared (NIR) spectrometer.

7. The non-destructive testing system of claim 6, wherein the receptacle includes at least one set screw to hold the second end of the optical fiber probe in place.

8. The non-destructive testing system of claim 6, wherein the first bundle of optical fibers is configured to carry the light from the NIR spectrometer to the probe tip and the second bundle of optical fibers is configured to carry the reflected light from the probe tip to the NIR spectrometer.

9. The non-destructive testing system of claim 8, wherein the receptacle includes a first opening to receive the first bundle of optical fibers and a second opening to receive the second bundle of optical fibers.

10. The non-destructive testing system of claim 1, wherein the insertion tube includes a second channel extending from the first end to the second end of the insertion tube, and wherein the second channel is configured to receive a second probe.

11. The non-destructive testing system of claim 10, wherein the second probe is one of a borescope probe and a hardness probe.

12. The non-destructive testing system of claim 1, wherein the insertion tube includes at least one notch to provide an indication of a depth of insertion of the probe tip into the rocket.

13. The non-destructive testing system of claim 1, wherein the non-destructive testing system further comprises a Near Infrared (NIR) spectrometer optically coupled to the optical fiber probe, and wherein the NIR spectrometer is configured to identify a status of the propellant.

14. The non-destructive testing system of claim 13, wherein the NIR spectrometer includes a handheld NIR spectrometer.

15. The non-destructive testing system of claim 13, wherein the NIR spectrometer is configured to identify the status of the propellant at least in part by identifying a percentage mass of at least one primary ingredient in the propellant.

16. A method of non-destructively testing propellant inside a rocket, the method comprising:

removing a payload and an ignition charge from the rocket to expose an ignition charge mount of the rocket;

mating a support sleeve to the ignition charge mount, including bolting the support sleeve to the ignition charge mount on the rocket;

inserting an insertion tube into an opening of the support sleeve to extend a probe tip into the rocket;

optically coupling a Near Infrared (NIR) spectrometer to an optical fiber probe that extends through the insertion tube to the probe tip, wherein the optical fiber probe includes a first bundle of optical fibers that extend from the NIR spectrometer into the insertion tube and terminate at the probe tip, and a second bundle of optical fibers that extend from the NIR spectrometer into the insertion tube and terminate at the probe tip; and

operating the NIR spectrometer to take at least one NIR measurement of the propellant including carrying light from the NIR spectrometer along the first optical fiber bundle to the optical fiber probe, and carrying light reflected from the propellant to the NIR spectrometer along the second optical fiber bundle.

17. The method of claim 16, wherein operating the NIR spectrometer includes analyzing the light reflected from the propellant to determine a status of the propellant.