Rapid Terminal-Trajectory Planner for an Unpowered Reusable Launch Vehicle

Kluever, Craig A.; Horneman, Kenneth R.; Schierman, John D.

doi:10.2514/6.2009-5766

Cited by 22 publications

(15 citation statements)

References 8 publications

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“…From (6), it can be seen that many methods such as increasing range, increasing dynamic pressure, and adjusting drag coefficient could be adopted to dissipate surplus energy. The objective of S-turn phase is to consume energy by increasing flight range.…”

Section: Ground Track Range Prediction the Mechanical Energy Of Unpomentioning

confidence: 99%

“…Horneman and Kluever [5] have presented a TAEM guidance methodology that employs a trajectory planning algorithm that computes a feasible path from the current state to the desired ALI state without relying on a precomputed, stored database of neighboring TAEM trajectories. Kluever et al [6] have proposed an algorithm capable of rapidly generating a feasible TAEM path from the current state to the desired ALI state. Their path-planning algorithm adjusts the TAEM trajectory by iterating on two geometric parameters: the down-track location of the HAC and its radius.…”

Section: Introductionmentioning

confidence: 99%

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Guidance Law Design for Terminal Area Energy Management of Reusable Launch Vehicle by Energy-to-Range Ratio

Jiang

Yang

2014

Mathematical Problems in Engineering

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A new guidance scheme that utilizes a trajectory planning algorithm by energy-to-range ratio has been developed under the circumstance of surplus energy for the terminal area energy management phase of a reusable launch vehicle. The trajectory planning scheme estimates the reference flight profile by piecing together several flight phases that are defined by a set of geometric parameters. Guidance commands are readily available once the best reference trajectory is determined. The trajectory planning algorithm based on energy-to-range ratio is able to quickly generate new reference profiles for testing cases with large variations in initial vehicle condition and energy. The designed flight track has only one turn heading, which simplifies the trajectory planning algorithm. The effectiveness of the trajectory planning algorithm is demonstrated by simulations, which shows that the guided vehicle is able to successfully dissipate energy and reach the desired approach and landing glideslope target with small tracking errors.

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Section: Ground Track Range Prediction the Mechanical Energy Of Unpomentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Guidance Law Design for Terminal Area Energy Management of Reusable Launch Vehicle by Energy-to-Range Ratio

Jiang

Yang

2014

Mathematical Problems in Engineering

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“…These initial A & L states corresponded to the nominal end-state from our TAEM trajectory studies in [16]. to track the rapid pulled-up reference trajectory.…”

Section: Nominal a And L Trajectorymentioning

confidence: 99%

“…In this study, we impose random off-nominal initial conditions to changes in initial glide-efficiency factor, flight-path angle, dynamic pressure, and the altitude. The statistics of the random A & L initial conditions used in this paper are based on the end-conditions of the guided TAEM phase [16], which are summarized in Table 3. The statistics of all runway touchdown state errors are summarized in Table 4.…”

Section: Off-nominal a And L Trajectorymentioning

confidence: 99%

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Automatic Approach and Landing Trajectory Planner for Unpowered Reusable Launch Vehicle

Al-Bakri¹,

Kluever²

2017

AAST

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A new guidance scheme for the approach and landing (A & L) phase of an unpowered reusable launch vehicle (RLV) has been developed. The main advantage of the new guidance is the use of glide-efficiency factor as the independent variable to compute the geometrical flare parameters by a set of analytical functions. The trajectory-planning algorithm generates its reference geometry based on the steep and shallow subphases, respectively. During the steep segment, the quasi-equilibrium glide (QEG) solution, which assumes a constant dynamic pressure and flight-path angle during the flight, is used to create the flight reference while the shallow segment is defined by polynomial functions for altitude and dynamic pressure profiles. Standard linearization methods are used to design a closed-loop command in order to track the QEG profile. Furthermore, proportion-derivative (PD) control is used to modulate the lift coefficient during the flare flight. Once the reference trajectory is created, a closed-loop simulation is obtained to track the reference. Off-nominal conditions, in terms of change in initial glide-efficiency factor, dynamic pressure, flight-path angle, and altitude are tested using a Monte-Carlo simulation. The simulated results demonstrate the effectiveness of the proposed algorithm to land the vehicle successfully under large dispersions of glide-efficiency factor.

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Dynamic guidance of orbiter gliders: alignment, final approach, and landing

Fonseca

Dilão

2018

CEAS Space J

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Rapid Terminal-Trajectory Planner for an Unpowered Reusable Launch Vehicle

Cited by 22 publications

References 8 publications

Guidance Law Design for Terminal Area Energy Management of Reusable Launch Vehicle by Energy-to-Range Ratio

Guidance Law Design for Terminal Area Energy Management of Reusable Launch Vehicle by Energy-to-Range Ratio

Automatic Approach and Landing Trajectory Planner for Unpowered Reusable Launch Vehicle

Dynamic guidance of orbiter gliders: alignment, final approach, and landing

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