초록

A missile guidance system and method for guiding a missile, mainly horizontally flying, to pass a target at a desired passage height.

대표청구항 ▼

The invention claimed is: 1. A missile, comprising: a propulsion system; a target seeking system; an inertial navigation system; a missile steering system to adjust a vertical flight direction angle (y) of said missile in flight; and a missile guidance system connected to said target seeking system

The invention claimed is: 1. A missile, comprising: a propulsion system; a target seeking system; an inertial navigation system; a missile steering system to adjust a vertical flight direction angle (y) of said missile in flight; and a missile guidance system connected to said target seeking system, to guide said missile, based on information from said target seeking system, to pass a predetermined distance (hdes) above a target. 2. The missile according to claim 1, wherein said missile guidance system comprises a gamma-ref calculation unit to calculate a reference value of a vertical flight direction angle (γref) used to adjust a current vertical flight direction angle (γ) of the missile to cause the missile to pass the target at a desired passage height (hdes). 3. The missile according to claim 2, wherein said gamma-ref calculation unit calculates the reference value of the vertical flight direction angle (γref) based on the following parameters: an elevation angle (σ), a desired passage height (hdes), a line-of-sight rotation ({dot over (σ)}), and a missile velocity (V). 4. The missile according to claim 3, wherein said parameters are used to calculate the reference value of the vertical flight direction angle (γref) according to the following expression γ ref = h des ⁢ σ . V - σ . ( 5 ) 5. A missile guidance system for use in a missile, wherein said system is to guide said missile to pass a predetermined distance (hdes) above a target, the system comprising: a gamma-ref calculation unit to calculate a reference value of a vertical flight direction angle (γref) used to adjust a current vertical flight direction angle (γ) of said missile to cause the missile to pass the target at a desired passage height (hdes); and a missile steering system configured to adjust the current vertical flight direction angle (γ) of said missile to cause the missile to pass the target at a desired passage height (hdes). 6. The system according to claim 5, wherein said gamma-ref calculation unit calculates the reference value of the vertical flight direction angle (γref) based on the following parameters: an elevation angle (σ), a desired passage height (hdes), a line-of-sight rotation ({dot over (σ)}), and a missile velocity (V). 7. The system according to claim 6, wherein said parameters are used to calculate the reference value of the vertical flight direction angle (γref) according to the following expression γ ref = h des ⁢ σ . V - σ . ( 5 ) 8. A method for guiding a missile towards a target, the method comprising: setting a desired passage height (hdes); obtaining a value of current line-of-sight rotation ({dot over (σ)}); obtaining a value of current velocity (V); forming a reference value for a vertical flight direction angle (γref) as a function of desired passage height (hdes), line-of-sight rotation ({dot over (σ)}), velocity (V) and elevation angle (σ); and steering the missile such that the vertical flight direction angle (y) becomes closer to said reference angle (γref). 9. The method according to claim 8, wherein said forming a reference value for the vertical flight direction angle (γref) comprises use of the expression γ ref = h des ⁢ σ . V - σ . ( 5 )