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8932 Nagatomo (1997 AR4)
Classification: Main-belt Asteroid          SPK-ID: 2008932
Ephemeris | Orbit Diagram | Orbital Elements | Mission Design | Physical Parameters | Discovery Circumstances | Close-Approach Data ]

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Orbital Elements at Epoch 2459000.5 (2020-May-31.0) TDB
Reference: JPL 29 (heliocentric ecliptic J2000)
 Element Value Uncertainty (1-sigma)   Units 
e .06751135873388835 3.4982e-08  
a 2.930918712254733 1.3645e-08 au
q 2.733048407651837 1.0191e-07 au
i 1.31664545100102 3.1896e-06 deg
node 216.2562966487078 0.00016732 deg
peri 274.4705190249715 0.00016917 deg
M 229.9846218094806 2.6575e-05 deg
tp 2459662.405988253616
(2022-Mar-23.90598825)
0.00013723 TDB
period 1832.753625668238
5.02
1.2799e-05
3.504e-08
d
yr
n .1964257470060881 1.3717e-09 deg/d
Q 3.128789016857628 1.4566e-08 au
  Orbit Determination Parameters
   # obs. used (total)      2423  
   data-arc span      11101 days (30.39 yr)  
   first obs. used      1989-07-29  
   last obs. used      2019-12-20  
   planetary ephem.      DE431  
   SB-pert. ephem.      SB431-N16  
   condition code      0  
   norm. resid. RMS      .47859  
   source      ORB  
   producer      Otto Matic  
   solution date      2020-Feb-22 19:07:17  

Additional Information
 Earth MOID = 1.74805 au 
 Jupiter MOID = 1.89647 au 
 T_jup = 3.273 
[ show covariance matrix ]

Ephemeris | Orbit Diagram | Orbital Elements | Mission Design | Physical Parameters | Discovery Circumstances | Close-Approach Data ]

Physical Parameter Table
Parameter Symbol Value Units Sigma Reference Notes
absolute magnitude H 12.9   n/a MPO435784  
diameter diameter 7.360 km 0.137 urn:nasa:pds:neowise_diameters_albedos::2.0[mainbelt] (http://adsabs.harvard.edu/abs/2011ApJ...741...68M)  
geometric albedo albedo 0.206   0.035 urn:nasa:pds:neowise_diameters_albedos::2.0[mainbelt] (http://adsabs.harvard.edu/abs/2011ApJ...741...68M)  

8932 Nagatomo           Discovered 1997 Jan. 6 by T. Kobayashi at Oizumi.
Makoto Nagatomo (b. 1937) is a pioneer in the field of electric propulsion. Today's electric propulsion technology, applied to Japan's sample return mission Hayabusa, is inherited from his work in the new realm.
NOTE: some special characters may not display properly (any characters within {} are an attempt to place the proper accent above a character)
Reference: 20031110/MPCPages.arcLast Updated: 2004-03-31

[ show close-approach data ]
Alternate Designations
 1997 AR4 = 1975 VH4 = 1982 BB3 = 1990 TZ3 = 1995 WV26 
Ephemeris | Orbit Diagram | Orbital Elements | Mission Design | Physical Parameters | Discovery Circumstances | Close-Approach Data ]
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