Abstract
Recent researches on hypersonic vehicles adopted in military have gained a lot of interest because of its high flight speed and efficiency. However the guidance laws for hypersonic missiles against the anti-missile system to increase survivability and defense penetration ability are still need to study. One main countermeasure to deal with this issue is to implement simultaneous attack. Therefore in this paper an impact-time-control guidance law for hypersonic missiles to impact a stationary target at the same desired final time is presented. Time-to-go estimation for time-varying velocity is derived by using a method of approximate acceleration form to extend the estimation method for constant velocity. The impact-time-control guidance law is firstly given and applied in vertical plane based on proportional navigation guidance law to control the impact time in terminal phase. Then the conditions that limit the method to apply are discussed. To overcome this issue, the guidance law applied in lateral plane is derived. The simulations are implemented using each method in vertical and lateral planes respectively and show good results for hypersonic missiles to achieve simultaneous attack.
Highlights
Hypersonic vehicles (HSVs) are usually considered to have speeds at Mach 5 and above while cruise altitudes are usually 80,000 feet (25 km) and above [1]
Developing impacttimecontrol guidance (ITCG) laws for hypersonic missiles to achieve simultaneous attack can be of great help to
The results show the ITCG law is valid to apply in lateral plane
Summary
Hypersonic vehicles (HSVs) are usually considered to have speeds at Mach 5 and above while cruise altitudes are usually 80,000 feet (25 km) and above [1]. The ITCG law was first suggested in [5] by Jeon for constant velocity missiles to impact stationary target. C. Zhu et al.: Impact-Time-Control Guidance Law for Hypersonic Missiles in Terminal Phase of pure proportional navigation guidance (PPNG) against stationary target without any linearization or approximation. In [14] Tekin presented an ITCG law based on polynomial look angle profile for constant speed missiles against stationary target. The time-to-go estimation is obtained by taking the value of any point in the flight to replace the initial value: sin λ R tgo = 1 + 10 V (29) This is the time-to-go estimation given in [5], the similar derivation procedure in some articles such as [20] for constant velocity situation. The integral equation is obtained by transforming (30) into differential form:
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