Northrop AQM-35

The AQM-35 was a supersonic target drone produced by the Northrop Corporation.

Q-4 / AQM-35
XQ-4
General information
Type	Target drone
National origin	United States
Manufacturer	Northrop Corporation
Primary user	United States Air Force
Number built	25
History
First flight	January 1956
Retired	mid 1960s

Overview

The AQM-35 program began life in 1953 as the Model RP-61 supersonic target drone. In June 1954 the United States Air Force awarded Northrop a contract for development of the project as the Q-4; the first flight-capable XQ-4 was launched in 1956.

The XQ-4 was capable of either ground or air launch, though the former mode was never tested. It was powered by a Westinghouse XJ81-WE-3 turbojet, allowing it to reach speeds of Mach 1.55. The drone's course was followed with radar, and flight commands were sent by a radio telemetry system. When the mission was completed the XQ-4 would deploy a three-stage parachute system along with four large inflatable airbags to cushion the impact with the ground.

The Air Force planned to use the Q-4 as a target for various surface-to-air and air-to-air missiles. A secondary reconnaissance function was planned, with TV or cameras carried. The drone was air-launched by a Lockheed DC-130 Hercules drone controller aircraft, or other carrier aircraft.

In 1963, the Q-4 family of drones were given the designation AQM-35A and AQM-35B. They were never considered entirely successful, with a variety of problems arising during both the development and flight testing phases. It was also considered that the flight performance of the drone was so high that it was not a realistic test for the missiles being developed––ironic since the whole point of the project was to develop a supersonic target. Only 25 of all types were ever built. The last examples of the type were retired during the 1960s.

Variants

XQ-4

Prototype of the RP-61 supersonic target drone.

Q-4

Production target drones.

Q-4A

Developed to use a Fairchild J83 engine and a modified radar signature for testing the CIM-10 Bomarc missile. When the engine could not be developed in time the variant was cancelled.

Q-4B

Fitted with a much more powerful J85-GE-5 engine and a strengthened airframe. This variant was first flown in 1961.

AQM-35A

Post 1962 designation of the Q-4 drone.

AQM-35B

Post 1962 designation of the Q-4B

Specifications (Q-4/AQM-35A)

General characteristics

• Length: 33 ft 0 in (10.06 m)
  

Q-4B/AQM-35B: 35.333 ft (10.77 m)

• Wingspan: 11 ft 1 in (3.38 m)
  

Q-4B/AQM-35B: 12.666 ft (3.86 m)

• Diameter: 1 ft 8 in (0.51 m)
• Height: 5 ft 7 in (1.69 m)
  

Q-4B/AQM-35B: 6.167 ft (1.88 m)

• Empty weight: 1,980 lb (898 kg)
  

Q-4B/AQM-35B: 3,400 lb (1,542 kg)

• Powerplant: 1 × Westinghouse XJ81-WE-3 Lightweight expendable turbojet, 1,810 lbf (8.1 kN) thrust
  

Q-4B/AQM-35B: 1x General Electric J85-GE-5 turbojet, 3,850 lbf (17 kN) thrust

Performance

• Service ceiling: 60,000 ft (18,000 m)
  

Q-4B/AQM-35B: 70,000 ft (21,336 m)

• Maximum speed: M1.55

Q-4B/AQM-35B: M2.0

See also

• List of missiles
• Unmanned aerial vehicle

References

• Northrop (Radioplane) Q-4/AQM-35