Measured surface temperatures of the Hayabusa capsule during re-entry determined from ground observation

Löhle, Stefan; Mezger, Andreas; Fulge, Hannes

doi:10.1016/j.actaastro.2012.11.004

Cited by 8 publications

(4 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…There is surge in NEAs mission activities, for which various space agencies around the world (e.g., NASA, European Space Agency, Japan Aerospace Exploration Agency, etc.) were commissioning researches about NEAs to determine the feasible exploration missions, including the (1) NEAR probe launched by NASA which can realize the fly-around to 433 Eros whose shape is like a potato with a size of 34.4 km × 11.2 km × 11.2 km and which verified the gravitational field model of 433 Eros and the stability of frozen orbit around the asteroid [3]; (2) the Hayabusa probe from JAEA which had successfully achieved to be attached and sample to the 25143 Itokawa (due to the smaller size and quality of the Itokawa asteroid, this mission realized the detection to the asteroid by hovering way [4]); (3) ROSETTA implemented by ESA which will arrive in the Churyumov-Gerasimenko comet in 2014 after a decade of interstellar flight and will make the comprehensive observation of the comet for a long time [5].…”

Section: Introductionsupporting

confidence: 56%

Neural Network Control for the Probe Landing Based on Proportional Integral Observer

Zhao

2015

Mathematical Problems in Engineering

View full text Add to dashboard Cite

For the probe descending and landing safely, a neural network control method based on proportional integral observer (PIO) is proposed. First, the dynamics equation of the probe under the landing site coordinate system is deduced and the nominal trajectory meeting the constraints in advance on three axes is preplanned. Then the PIO designed by using LMI technique is employed in the control law to compensate the effect of the disturbance. At last, the neural network control algorithm is used to guarantee the double zero control of the probe and ensure the probe can land safely. An illustrative design example is employed to demonstrate the effectiveness of the proposed control approach.

show abstract

Section: Introductionsupporting

confidence: 56%

Neural Network Control for the Probe Landing Based on Proportional Integral Observer

Zhao

2015

Mathematical Problems in Engineering

View full text Add to dashboard Cite

show abstract

“…In September 2007, the United States launched another probe, Dawn, to explore the Ceres and giant asteroids Vesta [7]. In March 2010, the Japanese asteroid explorer Hayabusa, which was launched on May 9, 2003, had returned to Earth and released a small capsule with the asteroid Itokawa into the reentry orbit [8]. In 2012, China published its asteroids exploration plan [9].…”

Section: Introductionmentioning

confidence: 99%

Asteroids Exploration Trajectory Optimal Design with Differential Evolution Based on Mixed Coding

Wang

Song

Dai

et al. 2015

International Journal of Distributed Sensor Networks

View full text Add to dashboard Cite

With the development of space technology, asteroid exploration will become a hotspot in the deep space exploration field. Space flight trajectory has the following requirements: needing a long time, having many engineering constraints, having a large number of targets, and having a series of feasible solutions. So how to find the global optimum flight program is the core issue of the deep space exploration trajectory design. This paper proposes a novel method to design the optimal trajectory by differential evolution (DE) algorithm for asteroid exploration based on mixed coding. In our method, the celestial sequence and the time sequence are coded together into the chromosomes of DE and optimized them simultaneously. The chromosomes are designed to include four parts: the celestial sequence, the exploration type, the time sequence, and the return time. The algorithm can make full use of the characteristics of the high efficiency and global optimization ability of differential evolution and can also avoid the problem of high complexity of the branch-and-bound algorithm and the problem of nonglobal optimal solution of the greedy algorithm. The algorithm is adopted to solve the Fourth Contest of National Space Orbit Design in China, and the result shows that both the computational efficiency and the performance of the algorithm are superior.

show abstract

“…The data for the two atomic O triplets and the N line at approximately 745 nm were integrated over the line width to illustrate the temporal change in intensity from each line in W · cm −2 . Loehle, Mezger and Fulge also gave a frame of IR spectra at a single trajectory point from the S2000 spectrometer and camera, which was ground-based [34]. The spectral irradiance plotted from 300 to 800 nm has a blackbody curve fitted at 3200 K, slightly higher than the value fitted by McIntyre et al but within the quoted error of ± 100 K [4].…”

Section: Hayabusa Re-entry Observation Missionmentioning

confidence: 94%

“…The HDVS1 instrument, operating from 410 to 470 nm, shows comparable results to AUS in terms of spectral irradiance and surface temperature. Winter et al also report the AUS data and discusses the HDVS1 data [35], and Loehle, Mezger and Fulge's spectra extends into the UV to overlap with AUS, but the spectra are too noisy below 400 nm to provide any useful information [34]. The spectra from Abe et al that overlapped with AUS was uncalibrated at the time of publication, and the visible spectra are not useful for the present work as it focuses on metallic species that come from paint or the spacecraft bus [26].…”

Section: Hayabusa Re-entry Observation Missionmentioning

confidence: 99%

Superorbital re-entry shock layers: flight and laboratory comparisons

Fahy¹

View full text Add to dashboard Cite

Hypervelocity re-entry through the Earth's atmosphere surrounds an aeroshell with a radiating shock layer, which has complex and potentially critical interactions with the thermal protection system, the key component to the vehicle's survival. Aerothermodynamic re-entry flight data is rare, but the available radiation data has potential for replication in ground-based experimental and numerical testing, where flight equivalent conditions can be achieved. A greater understanding and ability to demonstrate the behaviour of re-entry vehicles will allow increased confidence in pre-flight laboratory predictions, design iterations based on testing and simulation, and an overall reduction in the thermal protection system (TPS) mass, therefore increasing the mass available for scientific payload. This thesis aims to replicate flight data from the unmanned Hayabusa and Stardust aeroshell re-entries in expansion tube experiments and numerical simulations, and assess the similarities and differences in the results. The flight data is in the form of infrared (IR) and ultraviolet (UV) spectra emanating from the bow shock, as captured by air-and ground-based observation missions.The experiments were performed in the X2 expansion tube, a hypervelocity impulse facility capable of producing flight equivalent conditions over a scaled aeroshell model for a brief test time. Prior to optical imaging tests, the conditions were designed through an iterative combination of analytical, experimental and numerical methods, based on binary scaling and enthalpy matching. Emissions from the radiating shock layers were captured by IR and UV spectroscopy, as well as two-dimensional intensity mapping through a narrow wavelength band filter, but the measurements were oriented differently to flight. The axisymmetry of certain imaging planes enabled the transformation of line of sight integrated intensities into radial quantities, which could describe the forebody shock layer and result in an integrated intensity comparable with integrated flight spectra.Numerical simulations must first model the flowfield before radiation modelling is possible. Compressible flow computational fluid dynamics (CFD) simulations were performed for the Hayabusa and Stardust flight vehicles at the selected trajectory points, and scaled models at idealised and simulated inflow conditions. Radiation spectra calculations were performed along the same lines of sight as imaged in experimental spectra, and over the entire flowfield to be comparable to flight data and experimental 2D imaging.iii The flight, experimental and numerical data combined for a series of comparisons to test the hypotheses that under binary scaling, spectral radiance along a line of sight is invariant, and radiative intensity scales with the square of the length scale. Spectra comparisons between experiment and CFD, and CFD and flight, tested the first hypothesis, and integrated intensity comparisons between experiment and CFD, and experiment and flight, tested the second hypothesis. Favourabl...

show abstract

Measured surface temperatures of the Hayabusa capsule during re-entry determined from ground observation

Cited by 8 publications

References 9 publications

Neural Network Control for the Probe Landing Based on Proportional Integral Observer

Neural Network Control for the Probe Landing Based on Proportional Integral Observer

Asteroids Exploration Trajectory Optimal Design with Differential Evolution Based on Mixed Coding

Superorbital re-entry shock layers: flight and laboratory comparisons

Contact Info

Product

Resources

About