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Consider a lawn roller with a mass of 100 kg, a radius of 0.2 meters, and a radius of gyration of 0.15 meters. A force of 200 N is applied to this roller, angled at 60 degrees from the horizontal plane. What will be the angular acceleration of the lawn roller?
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Related Experiment Video

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Trajectory-Shaping Guidance with final speed and load factor constraints.

Wenbin Yu1, Wanchun Chen1

  • 1School of Astronautics, Beihang University, Beijing 100191, China.

ISA Transactions
|December 24, 2014
PubMed
Summary

This study presents a new guidance law for hypersonic gliding vehicles, ensuring precise targeting and speed control. The Trajectory-Shaping Guidance and Final-Speed-Control Scheme achieve a near-zero final load factor for safe landings.

Keywords:
Final-Speed Control SchemeGeneralized closed form solutionsLinear time-varying systemSpectral decompositionTrajectory-Shaping Guidance

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Area of Science:

  • Aerospace Engineering
  • Guidance, Navigation, and Control (GNC)

Background:

  • Hypersonic gliding vehicles (HGVs) require sophisticated guidance laws for terminal engagement.
  • Achieving precise final speed and minimizing load factors are critical for mission success and vehicle integrity.

Purpose of the Study:

  • To design and analyze a novel guidance law for HGVs targeting ground objectives.
  • To ensure a specified final speed and a near-zero final load factor during descent.

Main Methods:

  • Development of a guidance law comprising Trajectory-Shaping Guidance (TSG) and Final-Speed-Control Scheme (FSCS).
  • Derivation of generalized closed-form solutions for TSG using a linearized engagement model with arbitrary speed functions.
  • Analysis of guidance coefficients to determine the stability domain for achieving a zero final load factor.

Main Results:

  • The proposed guidance law effectively steers the HGV to the target while managing final speed.
  • The stability domain for guidance coefficients ensures a near-zero final load factor, independent of speed change rate.
  • Closed-form solutions for TSG are obtained, enhancing the predictability of the guidance system.

Conclusions:

  • The designed guidance law successfully meets the stringent requirements of terminal guidance for HGVs.
  • Proper selection of guidance coefficients within the derived stability domain guarantees a near-zero final load factor.
  • The methodology provides a robust framework for guiding hypersonic vehicles with precise terminal state control.