Verification of a Fully Numerical Entry Guidance Algorithm

Finite‐time trajectory tracking control for entry guidance

“…This hypersonic vehicle utilizes an offset of mass center to create a constant angle of attack, which can generate sufficient lift during peak heating and peak deceleration. 8,34 Neglecting centripetal acceleration from the Earth rotation, the hypersonic vehicle can be regarded as a point mass and the standard simplified equations of motion are 12,34 = V r cos sin cos ,…”

“…The vital mission of entry is to guide the vehicle to a predefined targeted point (parachute deployment point). 34 To ensure that the vehicle can land on the Earth safely and precisely, some strict conditions should be satisfied. Among these requirements, it has been reported that the parachute deployment altitude plays a vital role on the safety of the final landing.…”

Precision Guidance for Mars Entry with a Supersonic Inflatable Aerodynamic Decelerator

“…In [17,21], the bank angle profile is parameterized by a linear function or even a constant such that a single guidance parameter is adjusted. Recently, Lu et al [22] verified the Fully Numerical Predictor-corrector Entry Guidance (FNPEG) for both direct and skip entry missions. In order to satisfy the acceleration constraint for Mars entry, Zheng et al [23] developed a constrained predictor-corrector algorithm based on an exact-penalty method.…”

Automated Re-entry System using FNPEG

“…However, for Earth missions, atmospheric uncertainty is not as significant. FNPEG [6,7] provides a predictor-corrector algorithm that does not require the significant preflight tuning and optimization that the Apollo variants do.…”