JPH09210599A - Structure of connection of side thrustor ignition circuit in side thrustor type airframe - Google Patents

Abstract

PROBLEM TO BE SOLVED: To lessen sharply the number of wirings for connection of an ignition circuit with a side thrust part, the number of contacts of relays or semiconductor switches, the number of contacts of receptacles for safety and plugs for short circuit, and relays for short circuit, and thereby to attain simplification of a fitting operation, reduction of the weight and cutdown of the cost. SOLUTION: In a side thrustor type airframe having a side thrustor part constructed by providing a large number of small-sized rocket motors in the outer periphery of the intermediate part of the airframe, the small-sized rocket motors are disposed in the number of (m) in the direction of the axis of the airframe and in the number of (n) in the circumferential direction, in the number of (m)×(n) in total, and connected in a matrix, while the end parts of wirings in the direction of the axis of the airframe and the end parts of wirings in the circumferential direction are connected respectively to a power source for ignition through relays or semiconductor switches of X1 -Xm and Y1 -Yn , of an ignition circuit.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a wiring structure of a side thruster ignition circuit in a side thruster type flying body.

[0002]

2. Description of the Related Art Aerodynamic control of a flying object requires an expensive steering device to move a control surface.

However, in order to meet the recent demands for high speed and low cost of flying objects, inexpensive and fast responsive actuators have been required.

In order to meet the above requirements, as shown in FIG. 6, a large number of small rocket motors (ignition time: 0.5 to 200 ms) 2 are attached to a flying body 1 to form a side thruster section 3, and a small rocket motor is constructed. There is a side thruster type flying body that controls the movement of the flying body 1 by igniting 2 toward the outside. In the spacecraft 1 that uses a side thruster to change the route, 100 to 2 are attached to the outer periphery of the middle part of the airframe.
00 small rocket motors 2 are mounted, and the small rocket motors 2 are selectively ignited in synchronization with the rotation to change a predetermined path.

By the way, as shown in FIG. 7, the side thruster-type flying body is a side thruster which is separately used to energize each small rocket motor 2 of the side thruster section 3 from the ignition power source 8 for ignition. a relay or a semiconductor switch S ₁ to S _n selectively turned oN at a proper timing based on a command from the flight arithmetic and control unit provided in the mold flying object 1, thereby igniting a small rocket motor 2 .

In this system, for n small rocket motors 2, n relays or semiconductor switches, and (n + 1) for connecting the ignition circuit 4 and the side thruster section 3 are connected.
One wire is required (for example, for 100 small rocket motors, 100 relays or semiconductor switches and 101 wires are required).

As described above, due to the large number of wirings with the relays or semiconductor switches, the work of assembling and wiring the small rocket motor 2 is very troublesome, and there is a risk of incorrect wiring. In addition, when storing the side thruster type flying body and handling it on the ground,
In order to prevent the small rocket motors 2 from firing indefinitely due to static electricity or stray current, it is necessary to take safety measures to short-circuit the wiring from each small rocket motor 2.

Therefore, conventionally, as shown in FIG. 8, (n +
1) Prepare a receptacle 9 having a number of contacts and a short-circuit plug 10, and when storing and handling on the ground,
As shown, the short-circuit plug 10 is attached to the receptacle 9 to ensure safety, and the short-circuit plug 10 is removed for actual firing.

As another example of safety measures when this short-circuit plug 10 is inconvenient in actual handling or cannot be mounted, as shown in FIG. 9, wiring from the small rocket motor 2 to the short-circuit relay is performed. R ₁ provided to R _n, when in handling the storage and ground side thruster type flying object closes the short-circuit relay R ₁ to R _n, actually short-circuit relay R ₁ ~ immediately if or firing to fire Controlled to open R _n .

In this system, since n short-circuit relays and corresponding wirings are required for n small rocket motors, the wiring work is also troublesome, and the weight and cost are high. Has become.

[0011]

SUMMARY OF THE INVENTION Therefore, according to the present invention, the number of wires for connecting the ignition circuit and the side thruster portion, the number of relays or semiconductor switches, and the number of contacts of a receptacle for safety measures and a short-circuiting plug or short-circuiting are provided. It is intended to provide a wiring structure of a side thruster ignition circuit in a side thruster type flying body that can reduce the number of relays, simplify the assembly work, reduce the weight, and reduce the cost.

[0012]

One of the connection structures of the side thruster ignition circuit in the side thruster type flying body of the present invention for solving the above-mentioned problems is that a large number are provided on the outer periphery of the middle portion of the flying body. In a side thruster-type flying vehicle in which the side thruster part is configured by installing the small rocket motors, m small rocket motors are arranged in the axial direction, n in the circumferential direction, and a total of m × n are arranged in a matrix. , And the ends of the wiring in the machine axis direction and the ends of the wiring in the circumferential direction were connected to the ignition power source via the relays or semiconductor switches of X _{1 to} X _m and Y _{1 to} Y _n of the ignition circuit, respectively. It is characterized by that.

Another one of the wiring structures of the side thruster ignition circuit in the side thruster type flying body of the present invention is as follows.
In the connection structure of the side thruster ignition circuit in the side thruster type flying vehicle with the above-mentioned configuration, the other end branch of each wire in the axial direction and the other end branch of each wire in the circumferential direction with one end connected to the ignition circuit The wiring is connected to the receptacle, and a short-circuit plug is attached to the receptacle.

Still another one of the wiring structure of the side thruster ignition circuit in the side thruster type flying body of the present invention.
One is the wiring structure of the side thruster ignition circuit in the side thruster-type flying vehicle with the above-mentioned configuration, in which the other end of each wire in the axial direction whose one end is connected to the ignition circuit and each wire in the circumferential direction are connected. The other end branch wiring is connected via a short-circuit relay.

Another one of the wiring structures of the side thruster ignition circuit in the side thruster type flying body of the present invention is as follows.
In the connection structure of the side thruster ignition circuit in the side thruster-type flying vehicle having the above-mentioned configuration, each relay or semiconductor switch of X _{1 to} X _m and each relay or semiconductor switch of Y ₁ to Y _n is a normally-on type. And none, X _{1 to} X
The branch wiring in the middle of the wiring connecting each relay or semiconductor switch of _{m to} the ignition power source and the other end branch wiring of the wiring connecting each relay or semiconductor switch of Y _{1 to} Y _n to the ignition power source are used as receptacles. It is characterized in that it is connected, a short-circuit plug is attached to this receptacle, and an ignition power switch is provided on a wiring between the receptacle and an ignition power supply upstream of the receptacle.

Still another one of the wiring structure of the side thruster ignition circuit in the side thruster type flying body of the present invention.
One is the connection structure of the side thruster ignition circuit in the side thruster-type flying vehicle with the above-mentioned structure, where X _{1 to} X
Each relay or semiconductor switch of _m and each relay or semiconductor switch of Y ₁ to Y _n is a normal-on type, X
Branch wiring in the middle of the wiring that connects each relay or semiconductor switch of _{1 to} X _{m to} the ignition power supply, and the other end branch wiring of the wiring that connects each relay or semiconductor switch of Y _{1 to} Y _n to the ignition power supply. Are connected by a short-circuit relay, and an ignition power switch is provided on the wiring between the ignition power supply and the upstream of the short-circuit relay.

[0017]

As described above, one of the connection structures of the side thruster ignition circuit in the side thruster type flying body of the present invention is that m × n small rocket motors are arranged in the axial direction and the circumferential direction of the flying body. And connect in a matrix manner, and the other ends of these wirings are respectively connected to X _{1 to} X _m and Y _{1 to} Y _n of the ignition circuit.
Since it is connected to the ignition power source via the relay or semiconductor switch of X, it is X based on the command from the flight operation / control device separately provided in the side thruster type flight vehicle.
By the ₁ to X _m and Y ₁ each from to Y _n most one selectively ON the relay or semiconductor switch, it is possible to ignite any small rocket motors. And
For (m × n) small rocket motors, (m +
n) an ignition circuit having a relay or a semiconductor switch and (m + for connecting the ignition circuit and the side thruster part)
n) The number of wirings is reduced to a fraction of the conventional one.

Further, in another one of the wiring structures of the side thruster ignition circuit in this side thruster type flying body, the number of contacts of the receptacle and the short-circuiting plug provided for safety measures is ( (m + n) lines are sufficient, and the number is significantly reduced as compared with the conventional one.

Further, in still another wiring structure of the side thruster ignition circuit, the number of relays provided as a safety measure may be (m + n), which is much smaller than the conventional one.

Further, in another one of the connection structures of the side thruster ignition circuit, the relays or semiconductor switches of X _{1 to} X _m and Y _{1 to} Y _n are of a normal on type, and X ₁
Connect to X _m of the relay or wiring having a relay or semiconductor switch of the branch wiring and the Y ₁ to Y _n of wires having a semiconductor switch and the other end branch lines to the receptacle, so wearing the shorting plug into the receptacle The number of contacts between the receptacle and the short-circuit plug may be two, and even if an ignition power switch is added, the safety measure device is extremely simplified.

Further, in another one of the wiring structures of the side thruster ignition circuit, a normal-on type X is used.
_Since the branch wiring of the wiring having _{1 to} X _m relays or semiconductor switches and the other end branch wiring of the wiring of the normally-on type Y ₁ to Y _n relays or semiconductor switches are connected to the short-circuit relay, a short circuit occurs. The circuit for use is only one circuit, and even if an ignition power switch is added, the safety measure device is extremely simplified.

[0022]

BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of a wire connection structure of a side thruster ignition circuit in a side thruster type flying object of the present invention will be described. Flight 1 as shown in Fig. 6
A small rocket motor (ignition time 0.5-20
0 ms) 2 m rows in the axial direction, n rows in the circumferential direction, total
In a side thruster type flying body in which (m × n) pieces are provided to form the side thruster unit 3, a large number of small rocket motors 2 and an ignition circuit 4 are used as a common axis as shown in the development view of FIG. Wiring in the direction 5 ₁ , 5 ₂ , 5 ₃ , ... 5 _m
And a plurality of wirings 6 ₁ , 6 ₂ , 6 ₃ , ... 6 _n in the circumferential direction are connected in a matrix.

Wirings 5 ₁ , 5 ₂ , 5 ₃ in the machine axis direction,
...... The ends of 5 _m are respectively connected to the wirings 6 ₁ , 6 in the circumferential direction via the relays or semiconductor switches X _{1 to} X _m of the ignition circuit 4.
The ends of ₂ , 6 ₃ , ... 6 _n are Y ₁ to Y of the ignition circuit 4, respectively.
It is connected to the ignition power source 8 via an _n relay or a semiconductor switch.

In the connection structure of the side thruster ignition circuit thus constructed, X _{1 to} X are supplied based on commands from the flight calculation / control device separately provided in the side thruster type flying body 1. 1 from each of the relays or semiconductor switches of _{m and} the relays or semiconductor switches of Y _{1 to} Y _n.
Any small rocket motor 2 can be ignited by selectively turning on one relay or semiconductor switch.

In this embodiment, the ignition circuit 4 having (m + n) relays or semiconductor switches for the (m × n) small rocket motors 2 and the connection between the ignition circuit 4 and the side thruster section 3 are provided. Although (m + n) wirings are required, this is a fraction of that of the conventional (m × n) wirings, and the effect increases as the number of small rocket motors 2 increases. growing.

For example, 100 small rocket motors 2
If 10 are arranged in the machine axis direction and 10 are arranged in the circumferential direction, 20 relays or semiconductor switches and 20 wirings will suffice, which is ⅕ of the conventional method.

Next, another embodiment will be described with reference to FIG.
In this embodiment, in the wiring structure of the side thruster ignition circuit of the above embodiment, as a safety measure for preventing inadvertent ignition, one end of the wire is connected to the ignition circuit 4 in the axial direction 5 ₁ ,
5 _2, 5 _3, the other end branch wiring _{...... 5 m 5 '1, 5} ' 2,
5 _'3, ...... 5' _m and the circumferential direction of the wiring 6 _and 62,
6 _3, the other end branch wiring _{...... 6 n 6 '1, 6} ' 2, 6 '
_3, connected to the ...... 6 _'n into the receptacle 9, this receptacle 9 which was equipped with a short-circuit plug 10, which in the evening and in the storage and the ground of the side thruster type flying object 1 at the time in handling safety measures The number of contacts between the receptacle 9 and the short-circuiting plug 10 for the purpose is (m + n), which is significantly reduced as compared with the conventional method.

In a further embodiment shown in FIG. 3, in the wiring structure of the side thruster ignition circuit of FIG. 6, one end of the side thruster ignition circuit is connected to the ignition circuit 4 in the axial direction as a safety measure to prevent inadvertent ignition. line 5 _1, 5 _2, 5 _3, the other end branch lines 5 _{...... 5 m '1, 5'} 2, 5 '3, ...... 5' m and the circumferential direction of the wiring 6 _and 62, 6 _3, ...... 6 _n the other end branch line of 6 '
_1, 6 _'2, 6' _3, obtained by connecting a ...... 6 _'n through the short-circuit relay R, According to this, the safety at the time in handling storage and ground side thruster type flying object 1 The number of relays for countermeasures is (m + n), and the number of relays is significantly reduced compared to the conventional method.

In another embodiment shown in FIG. 4, in the wiring structure of the side thruster ignition circuit of FIG. 6, each of relays X _{1 to} X _m of the ignition circuit 4 is used as a safety measure for preventing inadvertent ignition. Alternatively, the semiconductor switch and each of the relays Y ₁ to Y _n or the semiconductor switch is not a normal-on type (normally ON) type, X
_{1 to} X _m relay or semiconductor switch and ignition power source 8
The branch wiring A in the middle of the wiring for connecting to and the other end branch wiring B of the wiring connecting the relays or semiconductor switches Y _{1 to} Y _n and the ignition power source 8 are connected to the receptacle 9, and the receptacle 9 The short-circuiting plug 10 is attached to the above, and the ignition power supply switch 11 is provided in the wiring between the ignition power supply 8 and the upstream of the receptacle 9.

In this embodiment, since each relay or semiconductor switch of X _{1 to} X _m and each relay or semiconductor switch of Y _{1 to} Y _n is of the normally-on type, the wiring of A and the wiring of B are receptacles. By connecting 9 and the short-circuiting plug 10, all the small rocket motors 2 are short-circuited, so that the safety of the storage of the side thruster type flying body 1 and the handling on the ground can be secured. The device therefor is significantly simplified.

The operation in the wiring structure of the side thruster ignition circuit of this embodiment is performed as follows.

First, when the side thruster type flying vehicle 1 is stored or handled on the ground, the short-circuiting plug 10 is attached to the receptacle 9 to prevent inadvertent ignition of the small rocket motor 2 due to static electricity or stray current. doing. At this time, the ignition power switch 11 is in the OFF state. Next, before the side thruster-type flying body 1 is launched, the short-circuit plug 10 is removed from the receptacle 9. Next, immediately before or immediately after the launch, the relays or semiconductor switches of X _{1 to} X _m and Y _{1 to} Y _n are separately attached to the side thruster type flying body 1.
It is controlled so that all of them are turned off by a command from the flight calculation / control device provided in. Next, the ignition power switch 11 is turned on. Then, one relay or semiconductor switch is selectively selected from the relays or semiconductor switches of X _{1 to} X _m and Y _{1 to} Y _n based on a command from the flight calculation / control device of the side thruster type flying vehicle 1. By turning it on, any small rocket motor 2
Repeat to ignite.

[0033] Yet another embodiment is shown in FIG. 5, in the connection structure of the side thruster firing circuit of FIG. 6, as a safety measure for preventing unforeseen fire, each of X ₁ to X _m of the ignition circuit 4 The relay or semiconductor switch and each of the relays or semiconductor switches of Y ₁ to Y _n are not normally-on type, and the relay or semiconductor switch of X _{1 to} X _m is connected to the ignition power source 8 in the middle of wiring. Branch wiring A and Y ₁ ~
Each of the Y _n relays or semiconductor switches and the other end branch wiring B of the wiring that connects the ignition power source 8 are connected by a normally-on (always-on) type short-circuit relay R,
An ignition power switch 11 is provided on the wiring between the ignition power supply 8 and the upstream side of the short-circuit relay R.

In this embodiment, the branch wiring A and the branch wiring B
Is connected by a short-circuit relay R that is always ON, all the small rocket motors 2 are short-circuited, and safety is ensured during storage of the side thruster-type aircraft 1 and handling on the ground. The device is significantly simplified.

The short-circuiting relay R is detected immediately before or after the side thruster type flying body 1 is launched, or after the launching is confirmed by detecting the starting acceleration of the flying body 1 or the roll of the flying body 1 It is turned off by a command from a flight computing / control device separately provided on the side thruster-type flying vehicle 1, and the relays or semiconductor switches of X _{1 to} X _m and Y _{1 to} Y _n are also flight computing / control devices. It is controlled to OFF by the command from. After that, the ignition power switch 9 is turned on, and one relay or semiconductor switch is selectively selected from the relays or semiconductor switches X _{1 to} X _m and Y _{1 to} Y _n based on the command from the flight calculation / control device. Turn it on and select any small rocket motor 2
Repeat to ignite.

[0036]

As can be seen from the above description, according to the wiring structure of the side thruster ignition circuit in the side thruster type flying body of the present invention, the number of wires for connecting the ignition circuit and the side thruster portion, The number of contacts of relays or semiconductor switches, receptacles for safety measures and short-circuit plugs, and short-circuit relays are greatly reduced. Therefore, the assembly and wiring work of the small rocket motor is facilitated, the risk of incorrect wiring is eliminated, the reliability is improved, and the safety measure device is extremely simplified to achieve weight reduction and cost reduction. .

[Brief description of drawings]

FIG. 1 is a diagram showing an embodiment of a wiring structure of a side thruster ignition circuit of the present invention.

FIG. 2 is a diagram showing another embodiment of the wiring structure of the side thruster ignition circuit of the present invention.

FIG. 3 is a diagram showing still another embodiment of the wiring structure of the side thruster ignition circuit of the present invention.

FIG. 4 is a diagram showing another embodiment of the wiring structure of the side thruster ignition circuit of the present invention.

FIG. 5 is a diagram showing yet another embodiment of the connection structure of the side thruster ignition circuit of the present invention.

FIG. 6 is a diagram showing a side thruster-type flying body.

FIG. 7 is a diagram showing a wiring structure of a side thruster ignition circuit in a conventional side thruster-type flying vehicle.

FIG. 8 is a diagram showing another example of a wiring structure of a conventional side thruster ignition circuit.

FIG. 9 is a diagram showing still another example of a wiring structure of a conventional side thruster ignition circuit.

[Explanation of symbols]

1 Side thruster type flying vehicle 2 Small rocket motor 3 Side thruster section 4 Ignition circuit 5 ₁ , 5 ₂ , 5 ₃ , ……… 5 _m Wiring in the axial direction 5 ′ ₁ , 5 ′ ₂ , 5 ′ ₃ , ...... _5'm Branch wiring 6 ₁ , 6 ₂ , 6 ₃ , ... 6 _n Circumferential wiring 6 ' ₁ , 6' ₂ , 6 ' ₃ , ... 6' _n Branch wiring 8 Ignition power supply 9 Receptacle 10 Short-circuit plug 11 Ignition power switch X ₁ , X ₂ , X ₃ , ... X _m Relay in the axial direction or semiconductor switch Y ₁ , Y ₂ , Y ₃ , ... Y _n Circular relay or semiconductor Switch R Short circuit relay A, B Branch wiring

Claims (5)

[Claims] 1. In a side thruster-type flying body in which a large number of small rocket motors are provided on the outer periphery of the middle portion of the flying body to form a side thruster section, m small rocket motors in the axial direction, in the circumferential direction. , And a total of m × n are connected in a matrix form, and the ends of the wiring in the axial direction and the ends of the wiring in the circumferential direction are respectively X _{1 to} X of the ignition circuit.
A wiring structure of a side thruster ignition circuit in a side thruster-type flying vehicle characterized in that it is connected to an ignition power source through _m and Y _{1 to} Y _n relays or semiconductor switches. 2. The wiring structure of the side thruster ignition circuit in the side thruster-type flying vehicle according to claim 1, wherein the other end branch wiring and circumferential direction of each wiring in the axial direction having one end connected to the ignition circuit. The wiring structure of the side thruster ignition circuit in the side thruster type flying body characterized in that the other end of each wiring is connected to a receptacle and a short-circuit plug is attached to this receptacle. 3. The wiring structure of the side thruster ignition circuit in the side thruster-type flying body according to claim 1, wherein one end of each wiring in the axial direction is connected to the ignition circuit. The wiring structure of the side thruster ignition circuit in the side thruster type flying body characterized in that the other end branch wiring of each wiring is connected via a short circuit relay. 4. The wiring structure of the side thruster ignition circuit in the side thruster type flying body according to claim 1, wherein each relay or semiconductor switch of X _{1 to} X _m and Y ₁ to X ₁ are connected.
Each relay or semiconductor switch of Y _n is a normal-on type, branch wiring in the middle of the wiring connecting each relay or semiconductor switch of X _{1 to} X _m and the ignition power source, and Y ₁ to Y
Connect each relay or semiconductor switch of _n and the other end branch wiring of the wiring connecting the ignition power supply to the receptacle, attach a short-circuit plug to this receptacle, and connect between the ignition power supply upstream of the receptacle. The wiring structure of the side thruster ignition circuit in the side thruster type flying body, characterized in that an ignition power switch is provided in the wiring. 5. A wiring structure of a side thruster ignition circuit in a side thruster-type flying vehicle according to claim 1, wherein each relay or semiconductor switch of X _{1 to} X _m and Y ₁ to X _m.
Each relay or semiconductor switch of Y _n is a normal-on type, branch wiring in the middle of the wiring connecting each relay or semiconductor switch of X _{1 to} X _m to the ignition power source, and Y ₁ to
Each relay of Y _n or the semiconductor switch and the other end branch wiring of the wiring connecting the ignition power source are connected by a short circuit relay, and the ignition power source switch is connected to the wiring between the ignition power source and the upstream of the short circuit relay. A side thruster ignition circuit wiring structure in a side thruster type flying body characterized by the provision of a.