Simulated payload apparatus for flight motion system testing

Patent metadata

Field	Value
Publication number	US-11346752-B2
Application number	US-201916710864-A
Country	US
Kind code	B2
Filing date	Dec 11, 2019
Priority date	Dec 11, 2019
Publication date	May 31, 2022
Grant date	May 31, 2022

Abstract

A simulated payload apparatus (SPA) for testing in a flight motion system (FMS), which has a body for mounting in the FMS, and which simulates an actual payload during the FMS test. The SPA may include a plurality of adjustable weights that are mountable on and/or removable from the body to vary the mass and/or center of gravity of the SPA. The SPA may include an adjustable bracket for interfacing with a motion drive of the FMS, in which the bracket is positionable along the body to vary the moment of inertia of the SPA. The SPA may include an onboard electronic measurement device that is configured to measure a motion characteristic of the SPA and/or communicate information about the measured motion characteristic in real-time during the FMS test. The SPA may include a laser alignment for aligning the SPA relative to test equipment of the FMS.

First claim

What is claimed is:

1. A simulated payload apparatus for testing in a flight motion system, the simulated payload apparatus comprising:
a body for being mounted in the flight motion system; and
a plurality of adjustable weights mounted on the body;
wherein the plurality of adjustable weights are mountable on the body and/or removable from the body to vary the mass and/or center of gravity of the simulated payload apparatus for simulating a corresponding actual payload during the flight motion system testing; and
wherein the simulated payload apparatus further comprises a bracket mounted to the body, the bracket being configured to interface with a motion drive of the flight motion system.

2. The simulated payload apparatus according to claim 1 , wherein the body includes a central body portion that is mountable in the flight motion system, and wherein the body includes first and second supports extending from the central body portion, wherein the adjustable weights are slidably mountable on the first and second supports.

3. The simulated payload apparatus according to claim 1 , wherein each of the plurality of adjustable weights has a fastening receiver for receiving a fastener that couples adjacent ones of the plurality of adjustable weights to each other.

4. The simulated payload apparatus according to claim 1 , wherein the plurality of adjustable weights have the same shape, or wherein at least some of the plurality of adjustable weights have a different shape.

5. The simulated payload apparatus according to claim 1 , wherein the plurality of adjustable weights have the same mass or density; or wherein at least some of the plurality of adjustable weights have a different mass or density.

6. The simulated payload apparatus according to claim 1 ,
wherein the bracket is an adjustable bracket;
wherein the adjustable bracket is configured to interface with a motion drive of the flight motion system; and
wherein the adjustable bracket is positionable along the body to vary the moment of inertia of the simulated payload apparatus for simulating a corresponding actual payload during the flight motion system testing.

7. The simulated payload apparatus according to claim 6 , wherein the bracket is slidably adjustable along the body.

8. The simulated payload apparatus according to claim 6 , wherein the bracket includes a plurality of circumferentially spaced apart clamps that clamp onto the body to fixably mount the bracket to the body during the flight motion system testing.

9. The simulated payload apparatus according to claim 8 , wherein the bracket further comprises a slip ring radially outwardly of the clamps, the slip ring being axially movable to move the clamps between a release position, in which clamps enable movement of bracket relative to the body; and lock position, in which the clamps engage the body to fix the position of the bracket relative to the body.

10. The simulated payload apparatus according to claim 9 , wherein the bracket further comprises a flange portion for interfacing with the motion drive, the flange portion having a plurality of tensioners that interact with the slip ring to axially move the slip ring, thereby moving the clamps between their lock and release positions.

11. The simulated payload apparatus according to claim 1 ,
wherein the simulated payload apparatus further comprises an onboard sensor mounted to the body;
wherein the onboard sensor is configured to measure a motion characteristic of the body during the flight system testing.

12. The simulated payload apparatus according to claim 7 , wherein the onboard sensor is part of an inertia measurement unit that is configured to sense and measure acceleration as the motion characteristic of the simulated payload apparatus during the flight system testing.

13. The simulated payload apparatus according to claim 12 , wherein the inertia measurement unit is configured to communicate, in real-time, information corresponding to the motion characteristic measured by the sensor.

14. The simulated payload apparatus according to claim 13 , wherein the inertia measurement unit is configured to communicate wirelessly via a wireless transmitter; or wherein the inertia measurement unit is configured to communicate with a wired connection via a communications interface.

15. The simulated payload apparatus according to claim 12 ,
wherein the inertia measurement unit is operably coupled to the body via a bracket; and
wherein a location of the inertia measurement unit and the bracket along the body is axially adjustable.

16. The simulated payload apparatus according to claim 1 ,
wherein the simulated payload apparatus further comprises an alignment fixture operably mounted to the body, and a laser mounted in the alignment fixture;
wherein the alignment fixture is adjustable to align a beam of the laser with the target wall to thereby enable alignment of the body relative to the target wall.

17. A flight motion system comprising:
a flight table; and
the simulated payload apparatus according to claim 1 .

18. A simulated payload apparatus for testing in a flight motion system, the simulated payload apparatus comprising:
a body for being mounted in the flight motion system; and
a plurality of adjustable weights mounted on the body;
wherein the plurality of adjustable weights are mountable on the body and/or removable from the body to vary the mass and/or center of gravity of the simulated payload apparatus for simulating a corresponding actual payload during the flight motion system testing;
wherein the simulated payload apparatus further comprises an alignment fixture operably mounted to the body, and a laser mounted in the alignment fixture; and
wherein the alignment fixture is adjustable to align a beam of the laser with the target wall to thereby enable alignment of the body relative to the target wall.

19. The simulated payload apparatus according to claim 18 ,
wherein the simulated payload apparatus further comprises an inertia measurement unit mounted to the body.

20. A flight motion system comprising:
a flight table; and
the simulated payload apparatus according to claim 18 .

Assignees

• Raytheon Co

Inventors

• Zamora Karla J
• Robledo Jaime
• Jones Richard
• Reyes Joel
• Raymond Devin
• Kokoulin Sergey
• Carman Daniel B
• Arefin Ashik

Classifications

• G01P13/00

  Indicating or recording presence, absence, or direction, of movement (electric switches H01H; counting moving objects G06M7/00) · CPC title

• G09B9/28 Primary

  Simulation of stick forces or the like · CPC title

• G01M99/007 Primary

  by applying a load, e.g. for resistance or wear testing (G01M99/001 takes precedence; testing the elasticity of structures G01M5/00) · CPC title