	US 12,223,848 B2
	Method for determining transition height elements in flight climbing stage based on constant value segment identification
Yingchao Xiao, Nanjing (CN); Weiyu Jiang, Nanjing (CN); and Yungang Tian, Nanjing (CN)
Assigned to THE 28TH RESEARCH INSTITUTE OF CHINA ELECTRONICS TECHNOLOGY GROUP CORPORATION, Nanjing (CN)
Filed by THE 28TH RESEARCH INSTITUTE OF CHINA ELECTRONICS TECHNOLOGY GROUP CORPORATION, Nanjing (CN)
Filed on Jul. 21, 2022, as Appl. No. 17/814,119.
Application 17/814,119 is a continuation of application No. PCT/CN2022/101833, filed on Jun. 28, 2022.
Claims priority of application No. 202111367778.2 (CN), filed on Nov. 18, 2021.
Prior Publication US 2022/0358846 A1, Nov. 10, 2022
Int. Cl. G08G 5/00 (2006.01); G05D 1/00 (2006.01)

CPC G08G 5/0065 (2013.01) [G05D 1/042 (2013.01); G08G 5/0039 (2013.01)]

10 Claims

1. A method for determining transition height elements in a flight climbing stage based on constant value segment identification, comprising a non-transitory computer readable medium operable on a computer with memory for the method for determining transition height elements in the flight climbing stage, and comprising program instructions for executing the following steps of:

step 1: for track data TR={tp_ii=1, . . . ,n} of one flight, wherein an i^thtrack point tp_iis denoted by one vector, tp_i=[ts_i, sp_i, ma_i], ts_i, sp_iand ma_irespectively denote a time, a speed and a Mach number of the current track point, respectively extracting a speed component and a Mach component from the track TR and recording the two components as a first speed component TR_{s_raw}and a first Mach component TR_{m_raw}; wherein, n denotes a total number of track points in the track data TR, and n is a positive integer;

step 2: expanding the first speed component TR_{s_raw}and the first Mach component TR_{m_raw}by adopting a linear interpolation method to obtain a second speed component TR_sand a second Mach component TR_m;

step 3: discretizing the second speed component TR_sof the track to obtain a discrete speed component TR_sd;

step 4: filtering each discrete value in the discrete speed component TR_sdaccording to a threshold thr, and acquiring a speed discrete value set SP;

step 5: identifying a constant-speed segment of the flight according to the speed discrete value set SP, and acquiring a maximum constant-speed value sp_cand a maximum moment ts_csof the constant-speed segment;

Step 6: keeping the Mach component of the track with a time no less than the ts_cs, in the second Mach component TR_mto obtain a third Mach component TR_{m_cut};

step 7: discretizing the third Mach component TR_{m_cut}of the track to obtain a discrete Mach component TR_md;

step 8: filtering each discrete value in the discrete Mach component TR_mdaccording to the threshold thr to acquire a Mach discrete value set MA;

step 9: identifying a constant-Mach segment of the flight according to the Mach discrete value set MA, and acquiring a constant-Mach value ma_ccorresponding to a minimum moment;

step 10: calculating a transition height H_transof the flight according to the maximum constant-speed value sp_cand the constant-Mach value ma_ccorresponding to the minimum moment; and

step 11: obtaining a real situation of the flight track and adjusting flying parameters of the flight based on results of the method for determining transition height elements in the flight climbing stage; which achieves fuel efficiency by controlling an aircraft in stratosphere with low air resistance, and facilitates real-time adjustment to resolve flight conflicts.