JP2639515B2 - Multi-stage flying object - Google Patents

Description

Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a multistage flying object in which a lower part and an upper part of the flying object can be separated.

2. Description of the Related Art As shown in FIGS. 11 and 12, for example, as shown in FIGS. 11 and 12, a lower body 54 and an upper body 55 of a flying body 51 having wings 52 or 53 are shown. After being fired and accelerated by the propulsive force of the lower part 54 from the launcher 56, the lower part 54, which is the first step, is cut off after a predetermined time has elapsed, and thereafter the upper part 55 alone is used alone. Some are known to keep flying.

After the separation of the lower section 54 and the upper section 55, the aerodynamic stability of the upper section 55, which is the second step, is maintained by the wings 53.

According to the conventional multistage flying vehicle as described above, the aerodynamic stability of the entire aircraft before separation is maintained by the wings 52, and no other aerodynamic stabilizing means is required. First, since the wings 53 on the upper stage 55 side function from the beginning, the air resistance increases due to the wings 53, resulting in loss of range and speed. As a result, there is a limit in extending the range and reducing the flight time.

SUMMARY OF THE INVENTION The present invention has been made in view of the above-described problems, and has as its object the purpose of making the upper-stage side wing a deployable type and deploying it only when necessary for the function of the air before separation. The purpose is to reduce resistance.

Means for Solving the Problems In the multi-stage flying object of the present invention, a stabilizing wing which is stored in the upper part of the flying object and which keeps the aerodynamic stability of the upper part after deployment is provided, and the wing is provided. When the lower and upper sections are combined, the above-mentioned stabilizer wings are stored inside the fuselage, and the aerodynamic stability of the flying body is maintained only by the lower section wings, while the lower and upper sections are separated. Is characterized in that a stable wing is deployed simultaneously with or immediately after the separation, and the aerodynamic stability of the flying object is maintained by the stable wing instead of the lower wing.

According to this structure, before the lower and upper sections of the flying object are separated from each other, the aerodynamic stability of the entire fuselage is maintained by the lower-stage wings. On the other hand, if the lower stage, which is the first stage, is cut off from the upper stage, the wings on the lower stage will be lost at the same time. The aerodynamic stability of the upper section, which begins to function and continues to fly independently, is maintained by the stable wing.

Embodiment FIGS. 1 and 2 are explanatory views showing the construction of an embodiment of the present invention. Reference numeral 2 denotes a rocket motor functioning as a lower portion of a flying object 1, and reference numeral 3 denotes, for example, a separation on the tip end side of the rocket motor 2. For example, a bullet is a payload such as a torpedo or the like, which is detachably coupled via a separating mechanism 4 using a nut party and functions as an upper portion of the flying object 1. The rocket motor 2 has a wing 5 at its tail, and a nose cap 7 containing a sequencer 6 for controlling the sequence processing of a stable flare 8 and a reduction gear 9 described later is attached to the tip of the payload 3. The flying object 1 is constituted by each element.

A plurality of deployable stabilizing flares 8 are provided at the rear of the payload 3 as stabilizing wings for maintaining aerodynamic stability of the payload 3.
In addition, a speed reducer 9 is provided. Flare 8 for each stabilization
Is the housing 10 on the payload 3 side as shown in FIG.
Are directed to the rotary shaft via a hinge pin 11 and are connected to one end of a direct acting actuator (cylinder) 12 provided independently for each stabilizing flare 8. Further, the actuator 12 is
Is connected to a gas generator 13 for supplying a predetermined gas to the gas generator.

When the function of the stabilizing flares 8 is not required, each stabilizing flare 8 is connected to the housing 10 as shown in FIG.
It is housed inside and is flush with the outer peripheral surface of the housing 10, thereby constituting a fuselage body with the outer peripheral surfaces of the housing 10 and the rocket motor 2. On the other hand, when the function of the stabilizing flare 8 becomes necessary, each stabilizing flare 8 is developed radially as shown in FIG. It serves to keep the aerodynamics stable.

As shown in FIGS. 3 and 4, a flapper 14 having a substantially U-shaped cross section, which constitutes a part of the stabilizing flare 8, is hinged to each stabilizing flare 8 by a pin 15 so as to be openable and closable. The flapper 14 expands with respect to the stabilizing flare 8 at the same time as the stabilizing flare 8 expands radially as shown in FIG. 3 to form an air inlet 16 in the stabilizing flare 8.

As shown in FIGS. 2 and 3, the speed reducer 9 is formed around an airbag 17 which can be deployed in the form of a parasol at the rear of each stabilizing flare 8. As shown in the figure, when the stabilizing flare 8 is in the retracted state, it is folded and stored inside the stabilizing flare 8.

As shown in FIG. 4, a plurality of flexible air tubes 22 are connected to the air bag 17 via bases 18, 19, washers 20, and cushioning material 21, and the other end of the air tube 22 is connected to a lock nut 23. Through the air inlet port 24 on the flapper 14 side
It is connected to the. Therefore, as shown in FIGS. 3 and 4, when the flapper 14 opens, the air intake 16
Is taken into the airbag 17 through the air tube 22, whereby the airbag 17 is deployed in a parasol shape.

That is, the speed reducer 9 operates in synchronization with the deployment operation of the stabilizing flare 8, and when the gas generator 13 is ignited and activated by a predetermined deceleration command during flight, the speed is generated by the gas generator 13. The stabilizing flare 8 is developed by the gas that is sent to the actuator 12, and the flapper 14 is simultaneously developed by the air.
Opens. While the aerodynamic stability of the aircraft is maintained by the deployment of the stabilization flare 8, the air intake by the ram pressure accompanying the flight
Air is blown into the airbag 17 from the airbag 16 through the air tube 22 to inflate and deploy the airbag 17, and serves to decelerate the body by the air resistance of the airbag 17.

Next, a specific operation method of the multistage flying object configured as described above will be described with reference to FIGS. 5 and 6 (A) and (B).

As shown in FIG. 1 and FIG. 5, the flying object 1 is fired from a launcher 25 on a ship or on the ground in a state in which a stabilizing flare 8 is stored. Let's fly while accelerating by the thrust. After the rocket motor 2 is completely burned, the rocket motor 2 performs high-speed ballistic flight toward the landing point on the sea surface 26. During this trajectory flight, turning or trajectory change may be performed as necessary.

When approaching the landing point, the sequencer 6 outputs a separation command for the rocket motor 2. In response to this separation command, the second rocket motor 2 and the second
The separation mechanism 4 shown in the figure is operated, and the rocket motor 2 is separated from the payload 3 as shown in FIG.

Simultaneously with or immediately after the separation of the rocket motor 2, the sequencer 6 outputs a deployment command of the stabilizing flare 8,
In response to this deployment command, the stabilizing flare 8 is deployed as shown in FIGS. 3 and 6 (A). That is, the gas generator 13 shown in FIG. 3 operates in response to the above deployment command, and the gas generated by the gas generator 13 is sent to the actuator 12, whereby the actuator 12 expands and each stabilizing flare 8 Expand radially. Due to the deployment of the stabilizing flare 8, the aerodynamic stability during flight by the flying payload 3 alone is maintained.

That is, the wings 5 (see FIG. 1) attached to the rocket motor 2 are lost simultaneously with the separation of the rocket motor 2.
The aerodynamic stability of the payload 3 is maintained by the deployment.

When the stabilizing flare 8 is deployed as described above, the flapper 14 attached to the stabilizing flare 8 opens at the same time, and the ram pressure accompanying the flight causes the air tube 16 to flow from the air inlet 16 to the air tube 22.
The air is blown into the airbag 17 of the reduction gear 9 through the airbag. As a result, the airbag 17 is inflated and deployed in the form of a parasol as shown in FIGS. 3 and 6 (B), and the payload 3 starts decelerating due to the air resistance of the airbag 17. Then, the payload 3 continues to fly while decelerating by the speed reducer 9, and finally, the swimsuit
You will rush.

7 and 8 show various embodiments of the present invention. In this embodiment, a plurality of stabilizing flares 32 which can be deployed around an axis 31 parallel to the machine axis are used as a payload 3.
When the function of the stabilizing flare 32 becomes necessary, each stabilizing flare 32 is developed radially around the shaft 31 as shown in FIG. 9 and FIG. It was made. In this embodiment, the same operation and effect as those of the first embodiment can be obtained, and when used in combination with a speed reducer, a parachute can be used instead of the airbag type speed reducer exemplified above. is there.

Effect of the Invention As described above, according to the present invention, when the upper stage and the lower stage of the flying object are coupled, the upper stage side stable wing is stored in the fuselage, and the upper stage of the flying object is After the lower part is separated from the wing and the wing attached to the lower part is lost, the upper wing part serves to maintain aerodynamic stability only after the stable wings stored on the upper part side are deployed. The air resistance when flying while the part and the lower part are joined can be made smaller than before, thereby extending the range and shortening the flying time.

[Brief description of the drawings]

FIG. 1 is a side view of a flying object showing one embodiment of the present invention,
2 is a cross-sectional view taken along the line II-II of FIG. 1, FIG. 3 is a cross-sectional view showing a state where the stabilizing flare and the speed reducer are deployed, FIG. 4 is an enlarged view of a main part of FIG. FIG. 5 is an explanatory view showing a specific operation method of the flying object of FIG. 1, FIGS. 6 (A) and (B) are explanatory views of the operation of a stabilizing flare and a speed reducer, and FIG. FIG. 8 is a view showing another embodiment, and FIG. 8 is a right side view of FIG. 7, FIG. 9 is a side view showing a state where the stabilizing flare of FIG.
10 is a right side view of FIG. 9, FIG. 11 is a side view showing an example of a conventional flying object, and FIG. 12 is an explanatory diagram showing a specific operation method of the flying object of FIG. 1 ... flying object, 2 ... rocket motor (lower part),
3 ... payload (upper part), 5 ... wings, 8, 32 ... stabilizing flares as stabilizers, 9 ... reduction gears, 16 ... air intakes, 17 ... airbags.

Claims (1)

(57) [Claims] 1. A multi-stage flying body in which a lower part and an upper part of a flying body are separably connected to each other, wherein the upper part of the flying body is stored in the airframe and the aerodynamic stability of the upper part after deployment. When the lower and upper sections with wings are connected, the above-mentioned stable wings are stored inside the fuselage, and the aerodynamic stability of the flying body is maintained only with the lower wings. On the other hand, after the lower stage and the upper stage are separated, the stable wings are deployed simultaneously with or immediately after the separation, and the aerodynamic stability of the flying object is maintained by the stable wings instead of the lower stage wings. A multistage flying object characterized by the following: