Table 2 The simulated object flight parameters from the given azimuth (θ) and elevation (γ)

From: Uncontrolled reentry of Low Earth Orbit Decaying Objects: a hidden threat to global safety and legal frameworks

θ

γ

Landing Lat.

Landing Lon.

Flight duration

Impact speed

(°)

(°)

(°)

(°)

(s)

(m/s)

135

−20

−1.1952

3.4933

551.9521

495.2152

 

−15

−1.5619

3.9075

570.6232

495.1254

 

−10

−2.2195

4.6248

598.3660

494.9047

 

−5

−3.8053

6.2937

650.5781

494.0572

 

0

−13.7728

16.7320

886.2906

478.6317

 

5

−44.8554

86.0340

1914.9172

330.7708

 

10

−41.4687

120.2883

2457.2084

353.0079

 

15

−39.3800

127.1461

2758.4374

366.1028

 

20

−39.6237

124.1084

2457.6936

7627.7722

315

−20

1.2000

1.1130

554.2473

495.2141

 

−15

1.5632

0.7975

572.6146

495.1251

 

−10

2.2123

0.2076

599.8210

494.9075

 

−5

3.7702

−1.2759

650.8172

494.0807

 

0

13.5333

−11.3213

880.9852

479.2035

 

5

44.8498

−81.0406

1913.8859

330.8085

 

10

41.4962

−115.5655

2458.0681

352.8321

 

15

39.3995

−122.5651

2760.0630

365.9832

 

20

39.6283

−124.0964

2457.4480

7627.6607

  1. The other initial parameters are: 0° latitude and 0° longitude, 7.5 km/s velocity, 100 km altitude. The abrupt transition observed between γ = 15° and 20° arises from the steep upward trajectory at high elevation angles, which can prevent the object from reentering within the simulation time frame and falls outside the intended reentry regime.
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