CN-121977386-A - Hanging flying throwing type modularized missile-borne guidance control cabin

CN121977386ACN 121977386 ACN121977386 ACN 121977386ACN-121977386-A

Abstract

The application relates to the technical field of missile-borne guidance control cabin design, in particular to a hanging flying throwing type modularized missile-borne guidance control cabin. The intelligent control system comprises a control cabin, wherein the control cabin internally comprises a flight control module, a navigation module and a power supply module, the flight control module, the navigation module and the power supply module are in butt joint through connectors to realize electric connection, and boards inside the modules are connected through flexible cables. According to the application, the problem that in the prior art, functional units are low in integration level, difficult to optimize in volume and weight and inconvenient to independently replace and maintain due to structural coupling only through the bottom plate and electrical connection depending on wiring of the bottom plate is solved by an interconnection mode of directly connecting the module indirect plug-in unit with the internal flexible cable, and the electric connection and mechanical locking between cabin sections can be simultaneously completed without an external cable network by means of the arrangement of the direct plug-in floating connectors at the two ends of the control cabin.

Inventors

ZHOU TAO
ZHANG QI
LIU ERJING
MA YAFEI
DONG YANMIN

Assignees

四川星际荣耀防务科技有限责任公司
星际荣耀航天科技集团股份有限公司

Dates

Publication Date: 20260505
Application Date: 20260327

Claims (10)

1. The utility model provides a hang and fly jettisoninging formula modularization missile-borne guidance control cabin which characterized in that includes: the control cabin (1) comprises a flight control module, a navigation module and a power supply module, wherein the flight control module, the navigation module and the power supply module are in butt joint through connectors to realize electric connection, and boards inside the modules are connected through flexible cables (2); The front end and the rear end of the control cabin (1) are respectively provided with a direct-insertion floating connector (3) which is used for being inserted with the front cabin section and the rear cabin section to realize electric connection and mechanical locking between the cabin sections; and a travel switch (4) is integrally arranged on the side wall of the control cabin (1), and the travel switch (4) is used for triggering and providing a T0 signal when the hanging, flying and throwing are separated.
2. The flying throwing type modularized missile-borne guidance control cabin according to claim 1, wherein the flying control module is at least integrated with functions of steering control, guidance calculation, flying safety control and on-missile power supply and distribution management; The navigation module comprises an inertial group (5), a guard receiver and a guard receiver antenna (6).
3. The flying throwing type modularized missile-borne guidance control cabin according to claim 1, wherein a drop-off socket (7) is further integrally arranged on the side surface of the control cabin (1), and the drop-off socket (7) is used for being connected with a plug of an airborne platform in a flying stage so as to realize power supply and bidirectional data communication of an aircraft; the falling-off socket (7), the travel switch (4) and the guide receiver antenna (6) are arranged on the same installation surface of the control cabin (1).
4. A flying throwing type modular missile-borne guidance control cabin according to claim 3, wherein the drop-off socket (7) is a mechanically separated drop-off socket (7) or an electrically separated drop-off socket (7).
5. The hanging flying throwing type modularized missile-borne guidance control cabin according to claim 1, wherein a first test port (8) and a second test port (9) are further arranged on the side face of the control cabin (1), the first test port (8) is used for ground test, initiating explosive device inspection and simulated power supply, and the second test port (9) is used for initiating explosive device safety control and non-unloading test of an elastomer in a transport case; The first test port (8) and the second test port (9) are respectively positioned on different sides of the control cabin (1).
6. The flying throwing type modularized missile-borne guidance control cabin according to claim 1, wherein a front hatch cover (10) is arranged at the front end of the control cabin (1), a rear hatch cover (11) is arranged at the rear end of the control cabin, the direct-insertion floating connector (3) is respectively fixed on the front hatch cover (10) and the rear hatch cover (11), and sealing strips are arranged between the front hatch cover (10), the rear hatch cover (11) and the control cabin (1) to realize cabin section sealing.
7. The flying throwing type modularized missile-borne guidance control cabin according to claim 6, wherein the in-line floating connector (3) on the front hatch cover (10) is configured with 5 paths of 28V power supply output, 5 paths of switching values, 1 path of CAN bus, 1 path of RS-422 bus and 6 paths of time sequence output signals; The direct-insert floating connector (3) on the rear hatch cover (11) is provided with 2 paths of switching value output signals.
8. A flying throwing modular missile-borne guidance control pod according to claim 3, wherein the drop socket (7) is configured with a platform power supply, a thermal battery (13) activation timing output, a 1-way CAN bus, a 1-way RS-422 bus, and an interlock signal.
9. The flying throwing type modularized missile-borne guidance control cabin according to claim 1, wherein an electromagnetic compatibility module (12) is further integrated in the control cabin (1), and the electromagnetic compatibility module (12) is electrically connected with the power supply module and is used for filtering a power supply and suppressing electromagnetic interference.
10. The hanging, flying and throwing type modularized missile-borne guidance control cabin according to claim 1, wherein the power supply module comprises a thermal battery (13) and a secondary power supply module, the thermal battery (13) is arranged on the rear end face of the control cabin (1), and the secondary power supply module is used for converting a primary power supply into multiple paths of secondary power supplies with different voltage levels and supplying power to the flying control module, the navigation module and the single-machine equipment on a missile according to a set power-on time sequence.

Description

Hanging flying throwing type modularized missile-borne guidance control cabin Technical Field The invention relates to the technical field of missile-borne guidance control cabin design, in particular to a hanging flying throwing type modularized missile-borne guidance control cabin. Background With the increasing requirements of modern warfare on the precise striking capability of weaponry, the performance of missile guidance control systems becomes a key factor in determining the effectiveness of the battle. As a core component of the missile, the guidance control cabin needs to have high accuracy, high reliability and strong information processing capability. At present, the following technical problems exist in the design and application of a guidance control cabin for hanging a flying throwing missile: 1. the functional units such as flight control, navigation and power supply are usually designed into independent circuit boards or modules respectively in the existing control cabin, and the functional units are electrically connected through a bottom plate or a back plate, so that all the functional units are only physically structurally coupled, the electrical connection depends on the wiring of the bottom plate, the overall integration level is low, the volume and the weight are difficult to optimize, and the independent replacement and maintenance of the modules are not facilitated. 2. The electrical connection between existing missile trunk segments is typically made by mating conventional connectors with an external cable network. During assembly, the plugging and mechanical locking of the cable network are required to be completed respectively, so that the operation steps are more and the efficiency is low. 3. In the flying throwing type missile, a travel switch for detecting separation of the missile and providing a T0 signal is adopted in the existing design, and the existing design is connected with a control cabin through an external cable network in a single placing mode. The external mode leads to a longer electrical link between the travel switch and the control system, and increases unreliable factors of signal transmission. Disclosure of Invention In view of the above, the invention provides a hanging fly throwing type modularized missile-borne guidance control cabin for solving the problems related to the background technology. The invention provides a hanging flying throwing type modularized missile-borne guidance control cabin, which comprises the following components: The control cabin comprises a flight control module, a navigation module and a power supply module, wherein the flight control module, the navigation module and the power supply module are in butt joint through connectors to realize electric connection, and boards inside the modules are connected through flexible cables; the front end and the rear end of the control cabin are respectively provided with a direct-insertion floating connector which is used for being inserted with the front cabin section and the rear cabin section to realize electric connection and mechanical locking between the cabin sections; And a travel switch is integrally arranged on the side wall of the control cabin and used for triggering and providing a T0 signal when the hanging, flying and throwing are separated. According to the application, the interconnection mode of direct connection of the module indirect plug-in unit and the internal flexible cable is adopted, so that the problems of low integration level, difficult optimization of volume and weight, and inconvenience in module independent replacement and maintenance caused by the fact that the functional units are only subjected to structural coupling through the bottom plate and the electrical connection depends on the wiring of the bottom plate in the prior art are solved, the problem that electrical connection and mechanical locking can be simultaneously completed between cabin sections without an external cable network is realized through the arrangement of direct plug-in floating connectors at the two ends of a control cabin, the problems of more assembly operation steps and low efficiency caused by the fact that a conventional connector is matched with the external cable network are solved, and the problem of increased unreliable signal transmission factors caused by the fact that the travel switch is singly placed and connected through the external cable network is solved by integrally installing the travel switch on the side wall of the control cabin. In an alternative embodiment, the flight control module is at least integrated with functions of rudder control, guidance calculation, flight safety control and on-board power supply and distribution management; The navigation module comprises an inertial measurement unit, a guard receiver and a guard receiver antenna. According to the application, the functions of originally scattered steering control, guidance, safety control, powe