Methods of connecting testing equipment to a missile system

Patent metadata

Field	Value
Publication number	US-9739568-B2
Application number	US-201514850141-A
Country	US
Kind code	B2
Filing date	Sep 10, 2015
Priority date	Sep 10, 2015
Publication date	Aug 22, 2017
Grant date	Aug 22, 2017

Abstract

A missile system includes a plurality of components, and a testing instrumentation platform secured within at least one of the plurality of components. The testing instrumentation platform is secured within the component(s) through at least one platform supporting adapter assembly. The platform supporting adapter assembly may include an adapter having a planar panel that supports one or more fasteners. The fastener(s) are configured to securely connect to a portion of a base of the testing instrumentation platform. At least one through-hole may be formed through a portion of the adapter. At least one tapered bolt is configured to be securely retained within the through-hole(s). The tapered bolt(s) securely connects the adapter to the component(s).

First claim

What is claimed is:

1. A missile system, comprising:
a plurality of components; and
a testing instrumentation platform secured within at least one of the plurality of components, wherein the testing instrumentation platform is secured within the at least one of the plurality of components through at least one platform supporting adapter assembly that comprises:
an adapter having a planar panel that supports one or more fasteners, wherein the one or more fasteners are configured to securely connect to a portion of a base of the testing instrumentation platform;
at least one through-hole formed through a portion of the adapter; and
at least one tapered bolt that is configured to be securely retained within the at least one through-hole, wherein the at least one tapered bolt securely connects the adapter to the at least one of the plurality of components.

2. The missile system of claim 1 , wherein the at least one of the plurality of components comprises at least one of a missile guidance set (MGS), a propulsion system rocket engine (PSRE), or a reentry system (RS).

3. The missile system of claim 1 , wherein the testing instrumentation platform is completely enclosed by the at least one of the plurality of components.

4. The missile system of claim of claim 1 , further comprising a main assembly that includes at least one booster stage.

5. The missile system of claim 1 , wherein the at least one platform supporting adapter assembly further comprises a connection block extending from a portion of the planar panel, wherein the at least one through-hole is formed through the connection block.

6. The missile system of claim 1 , wherein the at least one platform supporting adapter assembly further comprises a central protuberance that is configured to align the at least one platform supporting adapter assembly with the at least one of the plurality of components.

7. The missile system of claim 6 , wherein the central protuberance comprises a ramp connected to a shoulder.

8. The missile system of claim 1 , wherein the at least one tapered bolt is longer than a standard bolt used to connect the at least one of the plurality of components to another of the plurality of components.

9. The missile system of claim 1 , wherein the at least one tapered bolt comprises:
a head connected to a threaded portion; and
a tapered pin extending from the threaded portion, wherein the tapered pin downwardly tapers from a root to a distal tip, wherein the tapered pin is configured to be received and locked within a reciprocally-shaped portion of the at least one through-hole.

10. The missile system of claim 1 , wherein the at least one platform supporting assembly further comprises at least one isolator coupled to the at least one fastener, wherein a portion of the base of the testing instrumentation platform abuts the at least one isolator.

11. A platform supporting adapter assembly configured to securely support a testing instrumentation platform within one or more components of a missile system, the platform supporting adapter assembly comprising:
an adapter having a planar panel that supports one or more fasteners, wherein the one or more fasteners are configured to securely connect to a portion of a base of the testing instrumentation platform; and
at least one tapered bolt that is configured to be securely retained within at least one through-hole formed through a portion of the adapter, wherein the at least one tapered bolt is configured to securely connect the adapter to the one or more components.

12. The platform supporting adapter assembly of claim 11 , wherein the at least one platform supporting adapter assembly further comprises a connection block extending from a portion of the planar panel, wherein the at least one through-hole is formed through the connection block.

13. The platform supporting adapter assembly of claim 11 , wherein the at least one platform further comprises a central protuberance that is configured to align the platform supporting adapter assembly with the one or more components.

14. The platform supporting adapter assembly of claim 13 , wherein the central protuberance comprises a ramp connected to a shoulder.

15. The platform supporting adapter assembly of claim 11 , wherein the at least one tapered bolt is longer than a standard bolt used to connect at least two components of the missile system together.

16. The platform supporting adapter assembly of claim 11 , wherein the at least one tapered bolt comprises:
a head connected to a threaded portion; and
a tapered pin extending from the threaded portion, wherein the tapered pin downwardly tapers from a root to a distal tip, wherein the tapered pin is configured to be received and locked within a reciprocally-shaped portion of the at least one through-hole.

17. The platform supporting adapter assembly of claim 11 , further comprising at least one isolator coupled to the at least one fastener.

18. A platform supporting adapter assembly configured to securely support a testing instrumentation platform within one or more components of a missile system, the platform supporting adapter assembly comprising:
an adapter having a planar panel that supports two fasteners, wherein each of the two fasteners is configured to securely connect to a portion of a base of the testing instrumentation platform;
lower and upper isolators coupled to the each of the two fasteners, wherein the portion of the base is sandwiched between the lower and upper isolators;
a connection block extending from a portion of the planar panel, wherein two through-holes are formed through the connection block;
a central protuberance outwardly extending from the connection block, wherein the central protuberance comprises a ramp connected to a shoulder, wherein the central protuberance is configured to align the platform supporting adapter assembly with the one or more components; and
two tapered bolts that are securely retained within the two through-holes, wherein the two tapered bolts are configured to securely connect the adapter to the one or more components, wherein each of the two tapered bolts is longer than a standard bolt used to connect at least two components of the missile system together, wherein each of the two tapered bolts comprises: (a) a head connected to a threaded portion, and (b) a tapered pin extending from the threaded portion, wherein the tapered pin downwardly tapers from a root to a distal tip, wherein the tapered pin is configured to be received and locked within a reciprocally-shaped portion of one of the two through-holes.

Assignees

• Boeing Co

Inventors

• Dominguez Kevin

Classifications

• F42B35/00

  Testing or checking of ammunition {(apparatus for measuring the energy of projectiles G01L5/14)} · CPC title

• F41G7/001 Primary

  Devices or systems for testing or checking · CPC title

• F42B15/01

  Arrangements thereon for guidance or control ({steering arrangements F42B10/60}; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]) · CPC title