RU2012109848A - Rocket projectile with a remote laser fuse - Google Patents

Abstract

1. A missile with a remote laser fuse, comprising a housing with an explosive, a fuse, in the housing of which a power source, a detonator, a safety cocking mechanism, and an optical target sensor connected to the specified mechanism, characterized in that the optical target sensor contains an electronic a block of at least two receiving-emitting channels, each of which contains a pulsed optical radiation source and a photodetector connected to the electronic block, while the optical axis of the pulse of the optical radiation source and the photodetector forming the receiving-emitting channel are directed at an angle of ≤90 ° to the longitudinal axis of the munition in the direction of movement and are displaced relative to each other, mainly parallel or almost parallel, and the distance between the optical axes of the emitter and photodetector is chosen from the condition l ≥ (d + d) / 2, where d and d are the largest diameters of the emitter and photodetector, respectively, while these receiving-emitting channels are placed around the longitudinal axis of the munition through p identical or almost equal angular gaps in the radial direction. 2. A missile with a remote laser fuse according to claim 1, characterized in that the required number of emitters / probe optical beams k in the optical target sensor is determined from the simultaneous fulfillment of the following conditions under which the height of the ammunition above the underlying surface is in the range h∈ [h, h ], where h = ƒ (ν, α, t) is the height above the underlying surface, ν is the rate of approach of the ammunition to the target / underlying surface, α is the angle of approach of the ammunition

Claims (4)

1. A missile with a remote laser fuse, comprising a housing with an explosive, a fuse, in the housing of which a power source, a detonator, a safety cocking mechanism, and an optical target sensor connected to the specified mechanism, characterized in that the optical target sensor contains an electronic a block of at least two receiving-emitting channels, each of which contains a pulsed optical radiation source and a photodetector connected to the electronic block, while the optical axis of the pulse of the optical radiation source and the photodetector, forming the receiving-emitting channel, are directed at an angle of ≤90 ° to the longitudinal axis of the munition in the direction of movement and are displaced relative to each other, mainly parallel or almost parallel, and the distance between the optical axes of the emitter and photodetector is chosen from the condition l ≥ (d _and + d _n) / 2, where d _and d and _n - largest diameters emitter and photodetector, respectively, said priemoizluchayuschie channels arranged around the longitudinal axis of the munition and through equal or almost equal angular gaps in the radial direction. 2. A missile with a remote laser fuse according to claim 1, characterized in that the required number of emitters / probe optical beams k in the optical target sensor is determined from the simultaneous fulfillment of the following conditions under which the height of the ammunition above the underlying surface is in the range h∈ [h _min , h _max ], where h = ƒ (ν, α, t) is the height above the underlying surface, ν is the rate of approach of the ammunition to the target / underlying surface, α is the angle of approach of the ammunition to the target / underlying surface; t is the time; h _max - the maximum given height of operation; h _min - the minimum specified height of the response, the distance to the underlying surface along the axis of the optical radiation $$L_i\left(t\right)=ƒ\left(\nu ,\alpha ,\beta ,{\varphi }_i\left({\varphi }_i^0,n,t\right),t\right)$$

where L _i is the distance to the underlying surface along the axis of the optical radiation, i = 1, ..., k; ν is the speed of the approach of the ammunition to the target / underlying surface; α is the angle of approach of the ammunition to the target / underlying surface; β is the angle between the longitudinal axis of the munition and the axis of the radiation pattern of the emitter — the angle of installation of the emitter; n is the frequency of rotation of the ammunition around the longitudinal axis; φ _{i is the} angle of rotation i of the emitter in a plane perpendicular to the longitudinal axis of the munition, and ( $${\phi }_i\left(t\right)\in \left[{\phi }_i^o,\left({\phi }_i^o+\frac{2\pi }{k}\right)\right];$$

Where $${\varphi }_i^0$$

- the initial angular position i of the emitter at the moment the ammunition reaches a height h _max , and $${\varphi }_i^0={\varphi }_{\mathrm{one}}^0+\left(i-\mathrm{one}\right)\frac{2\pi }{k}$$

, $${\varphi }_{\mathrm{one}}^0\in \left[0.2\pi \right]$$

; t is the time, is at least for one i emitter in the specified measurement range L _i (t) ∈ [L _min , L _max ], while $$\left(\left[t_{L_{\min }},t_{L_{\max }}\right]\cap \left[t_{h_{\min }},t_{h_{\max }}\right]\right)\le T$$

where T is the time interval of one working cycle of determining the distance. 3. A missile with a remote laser fuse according to claim 1 or 2, characterized in that the electronic unit implements an algorithm for the simultaneous operation of at least two receiving-emitting channels and checking for registration of target identification signals simultaneously on two or more simultaneously functioning receiving-emitting channels. 4. A missile with a remote laser fuse according to any one of claims 1 to 3, characterized in that the simultaneously functioning receiving-emitting channels used to check for the simultaneous registration of target identification signals are mounted around the longitudinal axis of the munition at a maximum angular distance from each other in a radial direction, mostly diametrically opposite.