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Canadian Bristol Aerojet Winnipeg Canada Proprietary Information CANADIAN BRISTOL AEROJET WINNIPEG CANADA PROPRIETARY INFORMATION This report includes information which is the property of Canadian Bristol-Aerojet Limited, Winnipeg and also information which was sup- plied by, and remains the property of, the Canadian Department of National Defence/Defence Research Board and shall not be used or duplicated without the written approval of the appropriate agency. REVISION 1, JUNE. 1962 For experiments at greater altitudes, the Black Brant IV-A is currently being developed. This is a two stage rocket with the Black Brant I motor boosting a Black Brant III vehicle to an altitude of 600 miles with a 40 pound payload. A further development of the 17" Black Brant II will be known as the Black Brant V. It is expected to have an altitude capability of 240 miles with 150 pounds of payload. A complete range of telemetry is being developed for this family of rockets together with appropriate launchers and other ground handling equipment. Figure 1.1 illustrates the various ranges of altitude of the Black Brant High Altitude Rockets together with the positions of some of the interesting areas of space, and experiments that can be achieved, with this series. NOTE: Propellant temperature range of —20°F to +120°F is listed in this brochure for the various Black 'Brant vehicles as being the Canadian Bristol Aerojet design objective. At present the solid propellant used in all of the Black Brant vehicles is cleared for storage and use from +30°F to +100°F. An evaluation program is currently underway to clear the propellant for storage and use from 10°F to +125°P and Canadian Bristol Aerojet intend to verify performance down to —20°F. REVISION 2. NOVEMBER, 1962 TABLE OF CONTENTS Section 1 INTRODUCTION Section 2 GENERAL DESIGN PHILOSOPHY Section 3 BLACK BRANT II Section 4 BLACK BRANT III Section 5 BLACK BRANT IV-A Section 6 BLACK BRANT V Section 7 INSTRUMENTATION Section 8 LAUNCHER EQUIPMENT Section 9 REVIEW OF THE CAPABILITIES OF BLACK BRANT FAMILY Section 10 CONVERSION FACTORS — WEIGHTS AND MEASURES Section 1 INTRODUCTION 1 INTRODUCTION The Black Brant Series of High Altitude Research Rockets is being developed specifically for the varied requirements of scientific and defence space research as a joint Canadian Government-Canadian Industry Program. This series of utility ve- hicles will initially cover an altitude range of between 100 miles and 600 miles with payloads of from 25 pounds to 300 pounds. Launching can be carried out over a wide temperature range and simple launching facilities are required. The team developing these vehicles is made up of the Canadian Department of Defence Production (DDP), The Defence Research Board (DRB). and Canadian Bristol-Aerojet Limited (CBA). The Canadian National Research Council (NRC), is also assisting in the design and development phases of the program. User agencies are monitoring the program and providing information to ensure the development of a product most suited to the requirements of all users. The solid propellant motor development including development of propellant, internal insulants, igniter and nozzle is being carried out by the Canadian Armament Research and Development Establishment (CARDE) of DRB. Process design, propellant filling and static testing is conducted by CARDE. Dynamic testing is conducted jointly by CBA and CARDE. The family of rockets known as the Black Brant series consists of a single stage 17" diameter rocket, one of 10" diameter, and a 2 stage vehicle which utilizes the 10" diameter rocket with a 17" diameter booster. The altitude range covered by these is the region above the limit of balloons and into the zone of satellites. The initial Black Brant vehicle was designed to a CARDE specification in 1956 to enable evaluation of the solid propellant motor to be carried out under dynamic conditions. The success of the dynamic test vehicle, known as the Black Brant I, led to its acceptance in Canada as a high altitude research rocket. A high degree of reliability has been experienced with the Black Brant I motor. The performance potential of the Black Brant I motor led to the development of a high altitude research vehicle with improved structural design, nose cone, and fins. This vehicle is known as the Black Brant II. The basic Black Brant II, referred to as the Black Brant 11-A, will carry a 150 pound payload to an altitude of 125 miles. Black Brant III, a 10" diameter rocket, provides a more economical approach to High Altitude Research. The design performance is an altitude of 120 miles with a 40 pound payload. REVISION 1, JUNE. 19&2 For experiments at greater altitudes, the Black Brant IV-A is currently being developed. This is a two stage rocket with the Black Brant I motor boosting a Black Brant III vehicle to an altitude of 600 miles with a 40 pound payload. A further development of the 17" Black Brant II will be known as the Black Brant V. It is expected to have an altitude capability of 240 miles with 150 pounds of payload. A complete range of telemetry is being developed for this family of rockets together with appropriate launchers and other ground handling equipment. Figure 1.1 illustrates the various ranges of altitude of the Black Brant High Altitude Rockets together with the positions of some of the interesting areas of space, and experiments that can be achieved, with this series. KILOS. MILES ISOOl Section 2 GENERAL DESIGN PHILOSOPHY 2 GENERAL DESIGN PHILOSOPHY A wide choice of motor sizes, methods of launching, attitude control, and coup- ling. etc. is available to the rocket designer. Any of the many combinations of these, results in a vehicle differing from the others in cost, complexity of construction, per- formance, reliability, etc. The basic vehicle characteristics that were chosen to govern the design of the Black Brant Rockets are the following, not necessarily in order of preference: (1) Performance (2) Availability and Utility (3) Reliability (4) Cost Effectiveness (5) Simplicity of Design and Launch Procedure (6) Launch Capability Over a Wide Range of Environmental Conditions. 2.1 PERFORMANCE Although there is a general requirement to cover the altitude zone from 30 kilometers (100,000 ft.) to 1500 kilometers (5,000.000 ft.), the main interest appears to be in the region up to about 1.000 kilometers (3,300,000 ft.) The initial design aim therefore, was to produce a family of vehicles to carry 40 pounds of payload up to 1,000 kilometers in altitude. 2.2 AVAILABILITY AND UTILITY The success of the CARDE propellant test vehicle suggested that this general design concept and the CARDE solid propellant should be the basis for the Black Brant family of research rockets. The 10" rocket was conceived for use as a single stage vehicle for requirements up to 650,000 feet. and as the second stage of the high altitude vehicle. Both basic rockets, therefore, have been designed for use either singly or with the minimum of modification as components of multi-stage vehicles. This increased the utility and usefulness of both. 2.3 RELIABILITY A high order of reliability is achieved by the combination of a proven motor and simplicity of design in staging and separation. 2.4 COST EFFECTIVENESS The purpose of the design was to produce the maximum performance with a minimum of cost. 2.5 SIMPLICITY OF DESIGN Although improved performance is possible by the use of some form of auto" mafic flight control system, it was considered that this would add to the complexity and cost. Since the requirement can be met without the use of this control, it was not included in the design approach. 2.6 LAUNCH CAPABILITY OVER A WIDE RANGE OF ENVIRONMENTAL CONDITIONS Simplicity of launching, coupled with the proven performance of the CARDE solid propellant engine over a wide range of environmental conditions, insures re- liability and ease of launching. Section 3 BLACK BRANT II 3 BLACK BRANT II 3.1 GENERAL Although this vehicle was developed from the Black Brant I under the overall design authority of CARDE. the marketing responsibility for the Black Brant II rests with CBA. It is a solid propellant, three finned, unguided sounding rocket designed for zero roll rate. The original Black Brant II vehicle is identified as the Black Brant 11-A. When equipped with a more recently developed CARDE solid propellant en- gine, the vehicle will be known as the Black Brant 11-B. 3.2 BLACK BRANT II.A DETAILS 3.2.1 CONFIGURATION The basic configuration as detailed in Figure 3-1 consists of: (1) Nose — conical followed by cylindrical section. (2) Motor — solid fuel, fixed nozzle. (3) Stabilizers — fixed fin. 3.2.2 NOSE The 86.0" long conical portion is followed by a 24.6" long cylindrical sec- tion. Approximately 6 cubic feet of volume is available for a maximum payload weight of 300 pounds. 3.2.3 ROCKET MOTOR The Black Brant II-A motor section is comprised of a solid propellant 15KS25000 rocket motor. 3.2.4 STABILIZERS Three fixed fins are used. Each fin has a leading edge sweepback of approxi- mately 55°, a trailing edge sweepback of 30°, with a semi-span of 30.4" and a root chord of 51.5". Total individual fin area is 1050 square inches. 3.2.5 COMPLETE VEHICLE The complete vehicle has an outside diameter of 17.2" and an overall length of 332.5". REVISION I.JUNE. 1962 3.2.6 WEIGHTS Weight of Loaded Rocket Motor. Inc. nozzlenozzle, , poundpoundss ......... .. 2.264 kilograms .... .. ........... ......1.027 Total Rocket Weight (less payload). poundspounds ..... .. ..... .. 2.550 kilogramskilograms .
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